CSAA/IET International Conference on Aircraft Utility Systems (AUS 2018)
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- Location: Guiyang, China
- Conference date: 19-22 June 2018
- ISBN: 978-1-78561-791-1
- Conference number: CP743
- The following topics are dealt with: system design of MEA at aircraft level, hydraulic power, electrical power, actuation systems, environmental control systems, onboard safety, rescue and protection system, landing gear and brake control, fuel systems, aviation physiology and ergonomics, fire protection, pneumatics, test equipment, ice protection (anti-icing and deicing), auxiliary power, utilities management systems, health monitoring, and other vehicle onboard functional systems.
- Session: A01 - System Design of MEA at Aircraft Level
- Session: A02 - Hydraulic Power
- Session: A03 - Electrical Power
- Session: A04 - Actuation Systems
- Session: A05 - Environmental Control Systems
- Session: A06 - Onboard Safety, Rescue and Protection System
- Session: A07 - Landing Gear and Brake Control
- Session: A08 - Fuel Systems
- Session: A09 - Aviation Physiology and Ergonomics
- Session: A10 - Fire Protection
- Session: A11 - Pneumatics
- Session: A12 - Test Equipment
- Session: A13 - Ice Protection (Anti-icing and Deicing)
- Session: A14 - Auxiliary Power
- Session: A15 - Utilities Management Systems
- Session: A16 - Health Monitoring
- Session: A17 - Other Vehicle Onboard Functional Systems
- Session: A18 - Other Mechatronics Systems
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- Author(s): Fengyu Jin ; Shaoping Wang ; Xingjian Wang
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(5 pp.)
Propulsion Controlled Aircraft (PCA) is an effective fault-tolerant control strategy when aircraft no longer controllable by normal aerodynamic means. PCA generates yaw torque by adjusting engine thrust to control the lateral/directional movement of aircraft. For large commercial aircraft, there are four engines. Differential thrust not only can be generated by external engine but can also be co-generated by internal and external engines. Therefore, this paper discusses the influence of different thrust allocation mode on PCA system in term of system response and economy. Through simulation and analysis, the optimal thrust allocation mode is obtained. - Author(s): Fu Cai ; Liu Pin ; Ma Yixin ; Wang huan
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(5 pp.)
This paper outlines the domestic and overseas more-electric/ all-electric technology development and the applications on the aircrafts and explores three more-electric technologies development situations and summarizes the advantages of the more-electric/ all-electric technologies against the traditional drive technologies. This paper researches the critical technologies of the most advanced more-electric scheme. Taking the example of the more-electric application in the flaps equipments, this paper completes the electric backup drive system modeling and verifies the reliability and feasibility of the more-electric aircrafts using the simulation technology. This paper states the suggestion to develop the airborne integration electric actuation system related technology research, i.e. the high performance permanent magnet, BLDC, the electrically driven pump and the integrated design, etc. - Author(s): Zhewen Tang ; Bo Yu ; Shuai Wu ; Zongxia Jiao
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(6 pp.)
With the use of electrically powered actuators in aircraft actuation system, the complexity increases in actuation architecture design process. Generally, it is hard to evaluate all the possible solutions within the limited design period due to the large solution space and numerous evaluation computation. In this article, a methodology assisting the aircraft actuation system design will be proposed. The methodology consists of two modules, Fault Tree Analysis(FTA) Module which is implemented for the analysis of system failure event, and Genetic Algorithm Optimization Module which provides a rapid exploration of optimal architectures based on reliability. The Expected Roll Control Effects is defined to compare the merits between architectures with the same reliability.
Thrust Allocation Modes Design and Analysis of Propulsion Controlled Aircraft
Research on A Power-by-wire - More-electric Actuation Technology
Aileron Architecture Exploration and Optimization Based on Reliability and Expected Roll Control Effects
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- Author(s): Jianhua Zhao ; Dianrong Gao ; Qiang Wang ; Bin Zhang ; Tao Chen ; Jingcheng Liu
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(6 pp.)
With the development of aviation industry, higher requirements are placed on the reliability and precision of aerospace components. Hydrostatic bearing technology is widely used in the aviation field. In this paper, the static pressure guide rail is taken as an example to study the calculation method of the bearing capacity of the static pressure bearing cavity, so as to obtain more accurate oil cavity bearing capacity, and then prepare for improving the reliability and precision of researching aerospace components. At present, the method called “Translating External Load” is generally used to analyze the bearing capacity of the oil pocket. Since the mechanics model of “Translating External Load” method varies with the variation arrangement of the oil pocket, so “Translating External Load” method has less commonality. According to the principle of superposition of force and the idea of converse thinking, the bearing capacity of the oil pocket with constant flow supply is divided into six parts, each part bearing the component of external load, and the mechanics model can be established. Based on the mechanics model built, the equation of the bearing capacity of each oil pocket can be derived with each load component acting on the hydrostatic slide. When the arrangement of the oil pocket is complicated, the computation of bearing capacity turns into the problem of statically indeterminate. Referring to the solution method of “Elastic Body”, the compatibility equations of deformations of oil film are presented, the statically indeterminate problem is translated into statically determinate problem, and the bearing capacity of each oil pocket is obtained. Vector superposition is carried to the six bearing capacity components of each oil pocket, and then the final equations calculating the bearing capacity of the oil pocket can be attained. The research work offers the general method for calculating the bearing capacity of the oil pocket, and the equations can be solved with the help of the computer programs and can improve the design efficiency and accuracy. - Author(s): Wu Si ; Yang Hualong ; Han Dingbang ; Chang Hai ; Huang Xiping ; Meng Qingtang
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(4 pp.)
In order to explore preliminarily if it is possible for hydraulic system of a certain type aircraft to remove heat exchanger, which can reduce the system weight and airline operation cost, and evaluate if hydraulic system temperature control strategy is too conservative. Heat generation and dissipation characteristics of hydraulic components in hydraulic powering system of a certain type aircraft is analyzed in detail, and thermal model of hydraulic powering system is created in AMESim in this paper. Oil temperature for hydraulic system with and without heat exchanger under typical working conditions is calculated, and system temperature without heat exchanger is compared with the design specification. Hydraulic powering system thermal analysis can be used as reference for system thermal design and optimization. - Author(s): Kang Ning ; Yin FeiXing ; Shi YouMin
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(7 pp.)
The research on response time of hydraulic Wing Tip Brake (WTB) is integrated with fluid, friction, electromagnetic and heat dissipation technology, this paper is mainly about the research and development on response time of hydraulic WTB for C919 aircraft High Lift System (HLS). First, the author uses SIMULINK virtual simulation to calculate the response time of the WTB, the simulation results show that main factors that affect response time are environmental temperature and fluid throttling, etc. secondly, according to the response time requirement of C919 aircraft high lift system at asymmetric fault, the author adds the throttle valve in the WTB hydraulic system to raise the product internal temperature, and uses ANSYS thermal simulation to analysis the WTB internal warming at low temperature; finally, the results of simulation analysis are verified by experiments. The experimental results show that the response time and thermal analysis coincide with the actual results, and meet the need for response time of C919 HLS to the hydraulic WTB. - Author(s): Qing Guo ; Yili Liu ; Qiang Wang ; Dan Jiang
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(7 pp.)
In this paper, an adaptive neural network (ANN) control is presented for a two degree of freedom robotic arm driven by electro-hydraulic actuator (EHA) with output constraints. ANN control is used to estimate the unknown model of a manipulator. A backstepping controller is designed, which ensures the stability of system and satisfies the dynamic tracking performance of EHA, where the convergence of closed loop system is strictly proved by Lyapunov method. Using the control method proposed in this paper, the signals are semi globally uniformly bounded in the closed-loop system, and the output constraints are not violated. The effectiveness of the presented controller is verified in the two degree of freedom robotic arm by the simulation results. - Author(s): Gao Dianrong ; Sun Ya-nan ; Liu Jingcheng ; Ma Hao
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(6 pp.)
In order to increase the loading capacity, reduce the friction and wear, prolong the life span of the port plate pair of the low-speed and high-torque seawater hydraulic motor, bionic non-smooth surface port plate with six kind of different dimple concaves has been conceived. Numerical simulation method has been applied to calculate the pressure distributions and loading capacities of the fluid film between the port plate with bionic non-smooth surface and end surface of motor rotor, the influence of the depth of dimple concaves, the form of dimple concaves and the rotor rotating speed on the loading capacities of the port plate pair has been analyzed. The results indicate that the loading capacities of bionic non-smooth surface port plate pair with the same rotating speed increase with the increasing depth of the pits. Under the same rotor rotating speed, the loading capacities of bionic non-smooth surface port plate pair with circular conical pit, square conical pit, circular hemispherical pit decrease almost linearly and slowly with the increasing depth of the pits. Under the same rotor rotating speed, the loading capacities of bionic non-smooth surface port plate pair with circular cylindrical pit, square cylindrical pit, triangle cylindrical pit decrease with the patterns of hyperbolic curve, and when the depth of the pit are equal and greater than 0.5mm, the loading capacities almost have the same values, but much less than the values of with circular conical pit, square conical pit and circular hemispherical pit. The work of the paper such as bionic non-smooth surface effects has some references for improving the loading capacity and anti-wear performance of the key tribopairs such swash plate/slipper, port plate/cylinder block and piston/cylinder block of the high pressure axial piston pump used in aircraft so as to promote the reliability and increase service life of the axial piston pump. - Author(s): Gao Dianrong ; Sun Ya-nan ; Xu Senhao ; Zhang Yan
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(5 pp.)
The finite element analysis software ANSYS was used to establish the two-dimensional finite element model of the stator and rotor of the axial piston hydraulic motor pump. The numerical calculation and analysis of the driving magnetic field were carried out. The result shows that the distribution of the magnetic field in the oil gap with hydraulic oil was uniform. The statics analysis of pump sleeve which is the key part of motor pump was performed through extracting the parameters of magnetic field torque and other data as the force conditions. It turns out that the distribution of the deformation, stress and shearing force of the pump sleeve under the stress condition was studied. It is concluded that the maximum deformation of the pump sleeve occurs at the shaft shoulder and at the end face of the pump sleeve positioning piston pump cylinder. The research provided reference and basis for the design and related calculation of motor pump. - Author(s): Gao Dianrong ; Liu Jingcheng ; Zhang Zongyi
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(5 pp.)
With the CFD method and orthogonal experiment method, the hydrodynamic lubrication performance of port plate pairs with Bionic Non-smooth Surface has been analyzed. Under the condition of guaranteeing that the sum of all the pithead area surfaces is the same in different bionic non-smooth, full water flow deputy hydrodynamic lubrication models has been established. The effect of rotating speed, pit sectional shape and pithead diameter on hydrodynamic loading capacity with concave bionic non-smooth surfaces is explored. It concludes that the influence of the three factors are in turn as follows: rotating speed is more important than pithead diameter, and pithead diameter is more important than pit sectional shape. Bionic nonsmooth surface is suitable for relatively high-speed conditions. Different sizes of pithead diameter have a great impact on pit hydrodynamic pressure-loading capacity. As pithead diameter increases, so does the load-carrying capacity of conical pit, cylinder pit, truncated-conic pit and spherical pit within limits. Among those pits, the pressure-loading capacity of bionic nonsmooth surface with conical pit performs best when the pit diameter is 1.6mm. High pressure axial piston pump is widely applied in aircraft, to improve the loading capacity and anti-wear performance of the key tribopairs such swash plate/slipper, port plate/cylinder block and piston/cylinder block is very important for promoting the reliability and increasing service life of the axial piston pump. Bionic non-smooth surface effects studied and the method employed in this paper could be used in the investigation of the key tribopairs of high pressure axial piston pump used in aircraft. - Author(s): Li Yang ; Jiao Zongxia ; Li Xinglu
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(6 pp.)
Linear drive collaborative rectification pump is designed for Electro-Hydrostatic Actuator to avoid the lateral force in axial piston pump. In nominal working condition, the volumetric flow ripple and dynamic reverse flow pulse are still inevitable. On one hand, the structural flexibility makes it possible to reduce the volumetric flow ripple by proposed control method, which is verified by simulation and experiment. On the other hand, by reference to axial piston pump, dead volume variation and valve slot are considered as approaches of reducing the dynamic reverse flow pulse, where dead volume variation method is proved infeasible due to collaborative rectification mechanism, and valve slot is effective and optimized to improve the performance. - Author(s): Shengrong Guo ; Pengfei Zhang ; Qinghe Zhou ; Dechen Sun ; Houtao Ku ; Chao Peng Xiaoping Ouyang
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(8 pp.)
The load simulation system is a subsystem of the reciprocating sealing test system, to evaluate the working life of the aircraft actuator's sealing components. In this paper, a synchronization controller based on bias coupling is developed to study the control characteristics of the multi-cylinder synchronization under the control of one servo valve. The dynamic model of the load is established and verified by simulations and experiments. The influences of friction, load, and etc. on the synchronization are also analyzed. And the results indicated that synchronization error can be effectively reduced using the controller, besides great cost savings. - Author(s): Meng Chen ; Lin Sun ; Songjing Li ; Changfang Zou
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(6 pp.)
The flapper-nozzle valve as the pilot stage of an electrohydraulic servo-valve used in the hydraulic control system is often troubled by the self-excited noise. The pressure pulsation can induce the oscillation of the flow field in the flapper-nozzle valve. This paper presents an experiment study of noise characteristics in a flapper-nozzle valve at sixteen different flow conditions with various inlet pressure pulsation conditions at different mean inlet pressures, 6 MPa, 8 MPa, 10 MPa and 12 MPa of the nozzle. In the experiments, for each mean inlet pressure of the nozzle, four groups inlet pressure pulsation conditions of the nozzle are considered. The pressure pulsation characteristics at the nozzle inlet and in the chamber of the flapper-nozzle valve and noise characteristics are measured and analyzed by using FFT method. Then, the comparisons of pressure pulsation characteristics and noise characteristics for these sixteen different inlet pressures (including all the mean inlet pressures and inlet pressure pulsation conditions) are carried out. The results confirm that the noise and pressure pulsation in the chamber of the flapper-nozzle valve are increased with the increment of the mean inlet pressures and inlet pressure pulsation conditions of the nozzle. This study reveals that the flow-acoustic resonance and resulting self-excited noise felt as squeal noise may occur when the pressure pulsation in the chamber of the flapper-nozzle valve is sufficient larger at the particular frequency. - Author(s): Guiyue Kou ; Xiaopin Yang ; Kanran Zhou
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(4 pp.)
In order to improve the sealing performance of the existing dry gas seal, a fishtail type bionic groove used for end seal is proposed in this paper. The geometric models of fish tail groove are structured and its mathematical models are analyzed. Based on the theory of computational fluid mechanics, the Reynolds equation of gas film between seal faces is established, and the numerical simulation study is carried out by the finite difference method. By using the analysis soft-ANSYS, the influence of the main geometric structure parameters of the fishtail groove on the sealing performance parameters, such as the opening force and the leakage amount, is emphatically analyzed. From the analysis of the simulation results, the optimum geometric structure parameters of the fishtail groove are obtained. The simulation results also show that the fishtail groove has larger opening force and smaller leakage. The overall bearing capacity and the film stiffness are better than those of the classical T groove. - Author(s): Wang Chuanli ; Hao Fei ; He Tao ; Zhou Dawei ; Yang Linjian ; Ma Ding ; Zhang Jingmin
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(6 pp.)
A new type of pure water hydraulic prop relief valve is designed. In order to improve its dynamic characteristics, the maximum dynamic stiffness is taken as the optimization objective, and the method of variable range optimization and genetic algorithm is used to optimize the spring stiffness Ks. Valve core mass m, core area A1, damping hole diameter d to optimize; The simulink simulation model of the safety valve is established and the output pressure curve is obtained in two cases. The results show that the optimization method is adopted: The optimum parameters can increase the dynamic stiffness of the relief valve by 20.6% and increase the output pressure by 10.6%, the dynamic performance of the relief valve with pure water hydraulic prop is greatly improved. - Author(s): Wen Zeng ; Hai Fu ; Songjing Li
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(5 pp.)
The pressure-driven device is designed to control the flow rates of the droplet microfluidic systems, which can eliminate the flow-rate fluctuations coming from the pump source. As monodisperse droplets are formed in the microchannel, periodic pressure fluctuations can be induced by the dynamic process of droplet formation, which can influence the stability and control precision of the pressure-driven flows. The effects of the pressure fluctuations induced by the droplet formation process on the dynamic characteristics of the open-loop and closed-loop control pressure-driven flows are comparatively studied. Particularly, a PT controller is integrated with the closedloop system and by properly choosing the parameters of the PT controller, the amplitude of the pressure fluctuations of the pressure-driven flows can be reduced drastically, which can increase the control accuracy of the driven pressure. Additionally, the effects of the container volume on the dynamic characteristics of the pressure-driven flows are also discussed. Most importantly, the study of the pressure-driven flows can be applied for the flowrate control of the fuel supply system of the aircrafts, and especially, steady supply of the fuel flow rates can be achieved for the aircrafts by the pressure-driven flows. - Author(s): Xiancheng Ji ; Yan Ren ; Hua wei
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(6 pp.)
The traditional high-frequency cleaning scheme can not effectively deal with large components. In order to solve this problem, a high-frequency electro-hydraulic cleaner is proposed. The key part is the 2D four-way valve. This cleaner working frequency can be controlled by the spool speed and amplitude can be controlled by the spool axial displacement. The cleaner uses the 2D four-way valve to drive the piston rod in the hydraulic cylinder and to achieve piston rod reciprocating motion. Then the piston rod to drive the box vibrate quickly and to remove the dirt on the surface of the cleaned object, to achieve the purpose of cleaning and achieve high-power cleaning. The visualization of real-time data collection, display and preservation are realized by the data acquisition system. In this paper, the prototype of the cleaner is modeled and both a theoretical study and experimental investigation are carried out. The results show that the high-frequency electro-hydraulic cleaner can realize high-power cleaning with the maximum working frequency of 2669Hz. The measured waveforms show varying degrees of distortion under the effect of hydraulic resonance below the resonant frequency (1903Hz). However, the measured waveforms has been little effected when the vibration frequency above the resonant frequency. This scheme which uses 2D four-way valve to achieve high-frequency electro-hydraulic vibration can be applied not only in the cleaner but also in other fields. - Author(s): Dong Li ; Sujun Dong ; Jun Wang ; Yunhua Li
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(6 pp.)
This paper deals with system-level temperature of the hydraulic system of the airliner. The power losses in airliner hydraulic system is converted to heat and results in the temperature rise of the hydraulic system. It seriously affects the safety and reliability of the airliner. In order to investigate thoroughly the mechanism of thermal load in airliner hydraulic system and control the temperature rise of airliner hydraulic system within an allowable range, this paper proposes two thermal management schemes which respectively adopt fuel/hydraulic oil heat exchanger or hydraulic pipeline passing through fuel tank. Then towards these two schemes it adopts lumped parameter method to conduct modeling and simulation from the angle of heat generation and dissipation for investigating the ability of thermal management scheme. Finally the simulation results show the temperature variation rule of hydraulic oil and demonstrate the validity of modeling method. - Author(s): Bing-ging Wang ; Xu-dong Peng ; Xiang-kai Meng
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(6 pp.)
The Elastomeric O-ring seal as a common reciprocating rod seal has been widely used in the aviation hydraulic system for preventing the hydraulic oil from contaminating the environment. When the hydraulic actuator is in the working process, the O-ring seal operates inherently in an unsteady operating condition. Therefore, an isothermal transient soft elastohydrodynamic mixed lubrication model that takes account of the effects of surface roughness and cavitation is implemented in this paper to predict the entire history of the seal performance, which is consisted of coupled fluid mechanics, contact mechanics and deformation analyses. The effects of the surface roughness of seals under different fluid viscosity are also discussed. The analysis results show that there is a critical rms roughness for the seal, below which the seal meets with zero leakage per cycle, but above which the seal will be in the leakage state. In addition, the critical roughness of seal surface is increases with the increasing fluid viscosity. - Author(s): Da-Wei Zhang ; Han-Jing Li ; Peng Dong ; Jing-Xiang Li ; Sheng-Dun Zhao
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(5 pp.)
This paper proposes a new damper for hydraulically interconnected suspension of which the reserve chamber takes the place of hydraulic accumulator so that the space for the accumulator is saved. The damper can be easily applied to reform the conventional suspension system for its space saving structure. The AMESim model of hydraulically interconnected suspension is established and simulations are implemented based on the damper. The results obtained show that, the overshoot and the settling time are decreased by 14.7% and 42.2% respectively and the largest roll angle and the steady roll angle are decreased by 9.9° and 5.9° respectively. Based on the AMESim models batch run on account of different pre-charged pressure values. In terms of the responses of the road excitation for different precharged pressure values, the best possible value of precharged pressure for the gas in reserve chamber is obtained. Moreover, the new hydraulic damper can not only be easily applied into the use of heavy load transportation but also in the landing gear for its space saving structure and the damping effect. - Author(s): Ma Yixin ; Fu Cai ; Ma Yixuan ; Guo Jukui
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(3 pp.)
With the development of servo control and information technology, the traditional actuators have been unable to meet the purpose of precise control of aircraft. As a signal detection and feedback device, the sensor enables the actuator to perform both safety monitoring and automatic control functions. Based on displacement sensor as the research object, this paper analyzed the key technology of displacement sensor. Through the application of displacement sensor, the key points in structural design are expounded, which proves that displacement sensor has the characteristics of high integration, high precision and so on. - Author(s): Zhang Hui ; Liu Hong ; Zhang Lei ; Li Wei
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(5 pp.)
The fluctuation and vibration resulting from the complex internal flow in the piston pump cannot be easily predicted using the traditional computational method. In this paper, numerical computational methodology for the flow characteristics of aviation piston pump based on multi-block structural grids is investigated. Firstly, the strategy and procedure of generating multi-block structural grids are proposed and grids for piston pump are carried out. Then, relative slip between cylinder and valve plate and reciprocating motion of piston are respectively simulated by sliding mesh method and dynamic mesh method, in which the axial velocity of dynamic boundary of pistons is defined by UDF program. Finally the validation case is implemented, and the validity and accuracy of numerical computational methodology are validated. In addition, the dynamic flow characteristics in the piston pump are analyzed, which can be applied to the analysis for the fluctuation or pressure impact or optimum design for flow path of piston pump. - Author(s): Kou Zhang Peng ; Li Zhen Shui ; Li Wei ; Wang Xing Jian
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(6 pp.)
The power calculation of the hydraulic system is very important in the design of the airborne hydraulic system. How to accurately calculate power is also a difficult problem. In this paper, the detailed power calculation process of the hydraulic system is proposed, and the concrete power calculation method is established. Taking a certain aircraft as an example, the power calculation process and method are applied and verified. - Author(s): Lu Liu ; Peng Zhang ; Shoujun Zhao ; Xue Xiao
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(5 pp.)
A test method for dynamic and static performances of Servo-Motor-Pumps (SMP) was proposed. As a new and high performance component for both power conversion and control, a SMP is critical for an Electro-Hydrostatic Actuator (EHA). However, there is still no accepted standard test method. An approach to measure both the flow curves and frequency responses was suggested, by testing a no-load EHA system where the SMP is installed. With a set of speed limits in position loop controller, the EHA step responses are tested, whose maximum output speeds can be derived by differentiating the output displacements and further the SMP flow outputs can be calculated that correlate the speed limits. A “speed command--flow output” curve is ultimately plotted. As the closed loop frequency response of a no-load EHA is implemented as conventionally, the open loop frequency response of the EHA system can be calculated and further the SMP frequency response can be deduced by eliminating the integration and the static gain in the control loop. The method and experimental data were given, demonstrating a simple and practical methodology to measure the dynamic and static performances of a SMP. - Author(s): Shengjie Fu ; Haoling Ren ; Tianliang Lin
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(6 pp.)
Though the two-cylinder four-stroke hydraulic free piston engine (HFPE) has advantages over the traditional HFPE in terms of fuel consumption and exhaust, its effective compression stroke which defines the compression ratio and the combustion is susceptible to the conditions of the intake valve. The force balance of the free piston assembly, the energy equation of the ideal gas in the combustion chamber and the relationship between the piston displacement and the angle of the intake valve were developed. The key parameters of the intake valve that influences the performance of the compression process were analyzed. The control flow chart of the intake valve was established according to the intake valve condition. The test rig was set up to verify the effectiveness and feasibility of the control. The results showed that no matter the initial angle of the intake valve is, the piston displacement almost overlaps and the piston can reach TDC almost at the same time. The angle of the intake valve and the servo motor are within the preset range when the intake valve closes and the piston reaches TDC despite of the changing of the initial angle of the intake valve. - Author(s): Yang Deng ; Yuanzhi Xu ; Zongxia Jiao
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(6 pp.)
To meet the requirement of higher power-to-weight ratio of new aircrafts, the pressure of hydraulic power system has been risen to 35MPa. Considering constant pressure pumps are mostly equipped as EDP(Engine-Driven-Pump) in aircrafts, the pressure of this type pump always maintain at a constant value. Long periods of high pressure running will cause energy waste and heat problems. In this paper, a variable-pressure pump with DDV(Direct-Drive-Valve) of multi-body spool is proposed. The design of multi-body spool and direct drive form can make manufacturing easier and structure compact. The mathematical and AMESim model are established to analyze the behavior of the variable-pressure pump. The results show that the output pressure of pump can continuously change between 21MPa and 35MPa with the command signal input, when the solenoid is power off, the pressure can still maintain at 21MPa , so the availability and reliability of the variable-pressure pump can be obtained. - Author(s): Wenxian Yang ; Xiangrong Xu ; Qinghe Zhou ; Bang Li
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(4 pp.)
Some aircraft steering actuator suffered a high failure rate in recent years, which increased its maintenance costs and lowered its reliability. In the study presented in this paper, the most common failure mode-oil leakage was analyzed. The failure causes were thoroughly analyzed. The influence of filling rate on oil leakage fault was studied in depth, finally feasible solutions were proposed and their rationality and reliability was verified by the simulation analysis and tests. - Author(s): Yan Wang ; Guiyue Kou ; Shuheng Hu
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(6 pp.)
As the power source of electro-hydrostatic actuator (EHA) system, high speed permanent magnet motor has small heat dissipation area and large heating power, which can easily lead to an extremely rapid temperature increase. For the heating problem, this paper researched the calculation of power losses and thermal modeling of EHA motor, in order to predict the temperature rise. First, heat transfer analysis for the motor is presented in this paper in which the heat flows inside and outside the motor is described precisely. Second, the power losses are calculated by Joule's law, Bertotti empirical formula and viscous friction theory respectively. Then, a 3D steady thermal model is developed with FEM, and validated by test results. Finally, the temperature rising behaviors of the motor and coolant oil are discussed through simulation results. The results show that the overall temperature rise goes down at first and then increase slightly with respect to the speed; the maximum temperature drop can up to 5 °C when outside air velocity increasing by 5 m/s. Besides, increasing the flow of coolant oil can remarkably reduce the temperature rise. - Author(s): Heran Zhang ; Junya Yin ; Xiaoping Ouyang ; Pengfei Zhang
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(5 pp.)
As a key component of the aircraft hydraulic system, the bootstrap reservoir can guarantee good self-priming of the pump at high rotation speed. This study provides the basic structure and working principle of the bootstrap reservoir. This paper analyzes the causes and characteristics of the reservoir burst. Through the co-simulation of AMESim and ANSYS workbench, the influence of the hydraulic impact on reservoir burst was observed, and the dangerous part where the bursting occurred was the piston rod. - Author(s): Xiaoqiong Du ; Vongliang Zhao ; Xiaoliang Yan ; Guohai Chen
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(4 pp.)
The optimization design of Yx-ring for a certain hydraulic actuator is studied. Firstly, parameterized model of Yx-ring is established by APDL language of ANSVS . Then, based on software ISIGHT, the main factors affecting the radial force and the maximum contact pressure on the lip are determined by the design of experiment. Furthermore, optimal shape of Yx-ring is achieved by virtue of intelligent optimization algorithm. Compared to the original structure, the total radial force at the lip of the new configuration is decreased by 13.9%, reducing the abrasion at the lip, the maximum contact pressure at the lip is increased by 16.8%, improving the sealing performance. The obtained optimization scheme provides a new idea for the design of other seal structures. - Author(s): Zhang Ruihua and Jiang Hongyan
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(4 pp.)
Airworthiness is crucial to the development of civil aircraft and is the premise and foundation for aircraft safety and commercial operations. Civil aircraft design started late in China. As civil aircraft downstream, suppliers of various system products are eager to know the validation of product airworthiness. πn this paper, the products whole life cycle is used as the starting point, the equipment test process is discussed, to show product delivery should not only be physical production in traditional sense, but also meet the equipment airworthiness requirements, and submit evidence documents in accordance with the requirements of the airworthiness review. At last, it takes SDP's impulse qualification test as an example to shows the whole life cycle of equipment qualification test. - Author(s): Huanhuan Li and Songjing Li
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(4 pp.)
The fluid-solid interaction phenomenon in the pilot stage of flapper-nozzle servo valve and armature assembly structural stress field is the main reason of self-excited noise and instability. The cavitation phenomenon is the main source of servo valve noise and cavitation erosion. In order to study the mechanism of transient cavitation in the pilot stage of flapper-nozzle servo valve, the three-dimensional model, ICEM CFD software was used for meshing, star-ccm+ simulation software was used to simulate the cavitation and flapper movement characteristics in the flow field under the pilot stage fluid-structure interaction dynamic characteristics of the servo valve. The results show that the fluid-solid interaction of the flow field in the flapper-nozzle pilot valve can cause the periodic change of cavitation in the flow field, and the increase of inlet pressure at the nozzle and the movement of the flapper will aggravate the cavitation phenomenon. The conclusions in this paper can provide theoretical basis for the stability of servo valve and the prevention of cavitation. - Author(s): Jiang Zhai ; Xuebo Liu ; Wenhui Xiao ; Lu Lang ; Ming Deng
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(5 pp.)
Based on the considerations of an additional angle on the swashplate, the inertia of moving slippers and pistons, the offset between cylinder barrel axis and swashplate rotating axis, the offset between piston ball center and swashplate reference plane, the driving torque model by all slippers on swashplate of the aeronautical hydraulic axial piston pump is created. The numerical calculation for a certain pump is taken as an example. From the result, ignoring inertial force can cause obvious calculation error for the torque. If the offsets are rationally designed, the slippers driving toque can rotating the swashplate to larger angle positon. If the swashplate is rotating, the rotating speed can affect the average value of the slippers driving torque. - Author(s): Liqun Xia ; Mingjun Zhu ; Wei Zhang ; Yafeng Song
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(7 pp.)
Power electric actuation technology is the inevitable demand of the new generation of aircraft energy optimization and management. It is an important key technology of multi / full electric aircraft, and it is an important guarantee for improving aircraft safety and improving maintainability. Over the past twenty years, theoretical and practical researches have proved that the use of power and electric actuators instead of hydraulic actuators is an inevitable trend. With the increasing maturity of multi electric and all electric actuators, it will speed up this development. As an important component of the power electric actuation system, the electric hydrostatic actuator technology is a typical representative of the successful application of the distributed hydraulic system. This paper will introduce the difficulties and key points of the comparison of EHA control technology, high speed wet-type PMSM's design and control in the development of EHA, and at the end of the article, give the dynamic and static test results of the EHA actuation system. - Author(s): Ma Jun ; Wang Jian ; Zhang Lei ; Li Zhenshui
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(7 pp.)
Aircraft hydraulic system requires that the structure of the hydraulic pipeline should be as light as possible and the stiffness and strength should be as higher as possible. However, the hydraulic pipeline always has the destructive stress such as vibration and pressure pulse, resulting in the aircraft on the hydraulic piping requirements are particularly high, This is a contradiction. Aiming at how to balance these contradictions, this paper studies the simulation and analysis of the stress and fatigue life of the pipeline under the condition of water hammer wave and vibration. First of all, a model of water hammer wave is established to simulate the pressure of the specimen. Then, the mathematical model of the vibration stress of the pipeline is set up, and the equivalent stress of the uniaxial force of the pipeline is calculated. The water hammer wave and the vibration superimposed stress curve are obtained. Finally, the fatigue life of the pipeline is simulated by fracture and damage mechanics. The research results show that the fatigue life of hydraulic pipeline coincides with the actual fault failure life under the condition of water hammer pulse and vibration superposition. - Author(s): Lei Han and Xiaojiao Zhao
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(5 pp.)
Aircraft plunger pumps provide pressurized fluid to manipulate rudders and landing gears of airplanes. The primary failure mode of aircraft plunger pump is abrasion of internal components. This paper proposes an abrasive wear model of aircraft axial plunger pump for estimating wear volume per unit time. Separation of valve plate and barrel is calculated by considering dynamics of barrel, and wear volume per unit time is estimated by a two-dimensional rhombic particle model. - Author(s): S.N. Shentu ; D.C. Jin ; B. Meng ; J. Ruan
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(4 pp.)
In order to meet the demand of light weight, high efficiency and high power density for aircraft, a novel twodimensional two-piston pump is presented. It applies a piston with two degrees of freedom for achieving the functions of oil distribution and oil suction and discharge, and it also use the way of mutual superposition of outlet flow from two pistons to eliminate flow pulsation. In terms of the volumetric efficiency, each piston chamber has four times of the motion of oil suction and discharge in a circle, and the pump is eight times more than a single plunger piston of axial piston pump. In detail, in the process of movement, there only produce the rolling friction between the roller and the curved rail. An experimental prototype is performed. Finally, text results indicate that when the rotation velocity is 5000r/min, the output flow can acquire 108.9L/min. - Author(s): Quan Lingxiao ; Zhang Qiwei ; Bai Ruxia ; Yang Le
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(8 pp.)
The continuous pursuit of high power to weight ratio of hydraulic system promotes the development of axial piston pump to high speed and high pressure, and puts forward more urgent demand for fluid vibration control method of the axial piston pump. In this paper, the mathematical model of axial piston pump fluid vibration transmission path was built up and two kinds of evaluation indexes were defined. At last the main fluid vibration transfer path was identified quantitatively. The method of fluid vibration transfer path analysis has an advantage for reflecting the transmission rule of fluid vibration inside the axial piston pump intuitively. The results can provide more pertinent guidance for the fluid vibration control of the axial piston pump. - Author(s): Quan Lingxiao ; Bai Ruxia ; Cui Chao ; Wei Jian
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(7 pp.)
Hydraulic system is widely used in aerospace, shipbuilding, heavy machinery and other industries. With the development of high pressure, high speed and high power to weight ratio, the mechanism of fluid solid coupling vibration is more complex. As a power transmission system, the fluid solid coupling of the hydraulic system will cause the system oscillation, reduce the reliability of the system operation, and even cause the pipeline rupture. The hydraulic system of pipeline as the research object, the establishment of fluid-structure interaction vibration equation of 14-model, study the influence of different simplified friction form of pipeline fluid-structure interaction vibration, and modal analysis and experiment. It provides some guidance for the study of fluid-structure interaction vibration. - Author(s): Guo Changhong ; Cui Chao ; Quan Lingxiao ; Zhang Qiwei ; Jiang Hongyan
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p.
(9 pp.)
The continuous pursuit of high power to weight ratio of hydraulic system promotes the development of axial piston pump to high speed and high pressure, and puts forward more urgent demand for fluid piston vibration control strategy of axial piston pump.In this paper, the transfer path analysis method is used to study the transfer characteristics of fluid vibration transmission path of different axial piston pumps. The analysis of the vibration transfer path directly reflects the difference in the transmission capacity of different transmission paths. The proposed method of transmission path analysis can provide more pertinent guidance for the vibration reduction and noise reduction of axial piston pump. - Author(s): Xinglu Li ; Zongxia Jiao ; Liang Yan ; Yaoxing Shang ; Tan Lei
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(4 pp.)
The novel collaborative rectification structure pump is a pump whose pistons are driven by linear motors directly to intake and exhaust oil, and the flow direction of oil is regulated with active collaborative rectification. The design of a linear drive motor requires a detailed understanding of the drive force of the pump. Meanwhile the accurate expression of driving force can also lay the foundation for the control of motor pump module. In this article, the driving force of the pump is divided into three parts, one is static pressure, the second is the friction force, flow force is third. This article focuses on the static pressure. An analytical formula for instantaneous pressure is established. The pressure variation curve is drawn. The simulation module of the novel collaborative rectification structure pump is established and the simulation results verified the accuracy of the analytic model. - Author(s): Huawang Sun ; Yaoxing Shang ; Shuai Wu ; Zongxia Jiao
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(5 pp.)
Due to asymmetry of the piston effective area on both sides of the single rod cylinder, its performances are limited compared to the double rod cylinder. In this paper, a novel electro-hydrostatic asymmetric actuator is proposed, in which double displacement pump is used to control the single rod actuator to improve system properties. The double displacement pump possesses two states, large displacement and small displacement, which respectively control rod less chamber and rod chamber. Mathematical and simulation models are constructed to analyze internal parameters of system. By analyzing force load curve, in case of no increase in maximum torque, rotating speed is reducing, that means power rating is lower. Furthermore amplitude-frequency and phase-frequency characteristics are enhanced. Effectiveness and availability of the design is authenticated. - Author(s): Jie Wang ; Chao Zhang ; Shaoping Wang ; Chao Zhang
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(6 pp.)
Performance of mechanical seal in piston pump is directly affected by thermal elastohydrodynamic lubrication. An accurate analysis of performance provides with theoretical foundation for further researches on its failure mechanism and remaining useful life. It's generally acknowledged that the oil wedge reflects the performance of seal. Researches on this field normally preset the thickness distribution of oil wedge and then continue study. But hypothetic wedge cannot display the real condition. In order to solve this problem, an original method is put forward in this paper depending on as less empirical equations as possible. Numerical simulation verifies the proposed models and obtains the results consisting of thickness of oil wedge, leakage rate and torque in different conditions, which in turn verifies the availability of the method if there are subsequent physical experiments. It's equally important that combining with finite element method, the proposed method can be applied to other types of mechanical seals which are made of different materials or having different structures. - Author(s): Chengyu Guo ; Shaoping Wang ; Chao Zhang
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(6 pp.)
Reciprocating seal is an important part of hydraulic equipment and is widely used in the actuator of the aircraft. Performance degradation analysis of them is becoming very important. At present, the researches on the performance degradation analysis of reciprocating seals at home and abroad are mainly focused on the theoretical research of sealing mechanism and experimental research on sealing performance. As the study of performance degradation based on the degradation data of reciprocating seals and the establishment of an effective performance degradation model can accurately describe the reliability of the reciprocating seal during its use. In this paper, Gaussian Copula function is used to establish the binary random correlation degradation model of the friction and leakage of the sealing surface of the reciprocating seal, and a Bayesian method is used to estimate the parameters. The proposed model is verified by performance degradation data of a certain type of reciprocating seal, and the results show that this model is accurate and effective. - Author(s): Li XiaoBin ; Shang YaoXing ; Wu Shuai ; Jiao Zongxia
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(4 pp.)
Electric Hydrostatic Actuator (EHA) is a highly integrated hydraulic system that is widely used in multi-electric and all-electric aircraft due to its high power density. One of the main constraints which limit increasing of EHA power density is the high heat output of the motor. This not only leads to an increase in the volume of the motor, but also increases the chance of thermal failure of the motor. In order to deal with the heat of the EHA motor, the international mainstream method is to increase the motor speed, reduce the motor current, thereby reducing the motor heating, but do not pay attention to the EHA motor running under the conditions of heat can be avoided. This article proposes an energy recovery EHA named ER-EHA, which can recover the hydraulic energy when EHA works in positive load conditions and release it when the load is reversed. This structure reduces the motor heating and improves the efficiency without affecting the dynamic characteristics of the EHA system. The improvement of the odds ratio have great application prospects in increasing the power density of EHA. - Author(s): Yan Zhou ; Shuai Wu ; Zewen Tang ; Zongxia Jiao ; P.C.-K. Luk
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(6 pp.)
Increasingly stringent environmental standards and economic challenges, fuel consumption, noise and pollution emissions have brought enormous challenges to aviation technology, and the need of changes and breakthroughs in this area has become more urgent. Distributed electric propulsion (DEP) is a revolutionary for future aircraft. Compared with the conventional power propulsion system, the aerodynamic structure and equivalent duct ratio of the DEP system have been significantly improved, and there are also significant reductions in noise, fuel consumption, and emissions. In this paper, Modelica is adopted to construct the models for DEP aircraft which is validated through simulation studies. The proposed models can then be used for further study on DEP aircraft. - Author(s): Bo Yu ; Shuai Wu ; Zongxia Jiao ; Yaoxing Shang
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(6 pp.)
Hydraulic system, one of the most important system in commercial aircraft, needs thorough testing procedures to validate security and economy requirements. Real-time simulation technology which is one of the most important procedures for testing and validation for hydraulic system designs can meet this demand. This paper establishes the realtime simulation platform of the hydraulic system of large commercial aircraft with the AMESim and VeriStand. The hydraulic system model built in AMESim, which is encapsulated into a dynamic link library file, will be downloaded to the Real Time (RT) operating system when joins the connection interface with VeriStand. The RT hydraulic system model can contact to aircraft control system with VMIC reflective memory network then it can check the flight safety on ground. The RT model transmits all the system state to a supervisor computer which is monitored by the developed graphics user interface. At the same time the supervisor computer sends command to the RT model to change system state which can be used as failure or damage cases. This platform has advantages in high flexible and high accuracy which has a great potential in aircraft hydraulic system design and validation. Three simulation tests are carried out to illustrate the effectiveness of the platform. - Author(s): Mingyang Li ; Yaoxing Shang ; Zongxia Jiao ; Xinglu Li
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(5 pp.)
Rotary vane actuators are widely used in load simulators, hydraulic simulation turrets, and rudder surface drives. The vane seal's performance directly determines the operating performance of rotary vane actuator. In this paper, a kind of composite rotary vane seals consisted of a rubber part and a polytetrafluoroethylene part is introduced. The sealing performance of a composite seal under 12MPa hydraulic pressure, including contact pressure and leakage evaluation, is analyzed based on ANSYS software. The results shows that the corner of the PTFE part has a worse performance compared with other parts of the composite vane seals. - Author(s): Bo Pang ; Shuai Wu ; Xiangyu Zhao ; Zongxia Jiao ; Tao Yang
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(6 pp.)
Aircraft braking system is a important subsystem for aircraft safety. Hardware-in-the-Loop (HiL) system is an important process for aircraft braking system study. It can be utilized to study control algorithm and validate the performance of braking before physical experiment which has advantages of low cost and rapid evaluation. In this study, a HiL system of aircraft braking system is established on the realtime operating system of RTX. By analyzing the stress situation of aircraft, the dynamic equations of aircraft, wheel, braking actuator, et. al. are presented. The temperature of braking disc is very important for the braking system, therefore, the thermodynamic equation of braking disc is also considered in the model. The nonlinear characteristics of friction force with slip-ratio and temperature is also modeled to increase the accuracy of the model. The models are a set of nonlinear differential equations which are calculated by the Runge-Kutta method. A subdividing integration step method is introduced to improve the simulation accuracy. The proposed model is validated by an aircraft braking system demonstration. The results indicate that the proposed HiL system has high accuracy and high flexibility which lay a foundation for studying of aircraft braking.
Indeterminate Mechanics Model for Bearing Capacity of Constant Flow Oil Pocket in Hydrostatic Slide
Thermal Analysis for Hydraulic Powering System of a Certain Type Aircraft
An Intelligent High Lift System Hydraulic Wing Tip Brake Response Time Optimization Research
Adaptive Neural Network Control of Two-DOF Robotic Arm driven by Electro-hydraulic Actuator with Output Constraint
CFD Simulation of Port Plate Pair Loading Capacity with Bionic Non-smooth Surface of Low-speed and High-torque Seawater Hydraulic Motor
Finite Element Analysis of Electromagnetic Field and Pump Sleeve of Axial Piston Hydraulic Motor Pump Based on ANSYS
Analysis on Hydrodynamic Pressure-loading Effect of Port Plate Pairs with Bionic Non-smooth Surface for Sea Water Low-speed and High-torque Hydraulic Motor
Reduction of linear drive collaborative rectification pump flow ripple
The Analysis of Multi-cylinder Synchronization in the Load Simulation System for Reciprocating Seals
Experiment Study of Noise in a Flapper-Nozzle Valve under Pulsing Inlet Pressure of the Nozzle
Design of a Biomorphic Groove Dry Gas Seal Based on Fishtail Outlines
Parameter Optimization for Dynamic Performance of a New Hydraulic Relief Valve in Coal Mine
Characterization of the pressure-driven flows for droplet microfluidics
Study on working characteristics of High Frequency Electro-hydraulic cleaner
Modeling and Simulation of System-Level Temperature for Airliner Hydraulic System in a Full Flight Mission Profile
Elastohydrodynamic lubrication characteristics of an O-ring hydraulic rod seal during transient operation
Study on a New Damper for Hydraulically Interconnected Suspension and Its Response Characterization
Integration of the displacement sensor in the actuator
Investigation on Numerical Computational Methodology for the Flow Characteristics of Aviation Piston Pump
Research on Power Calculation of Airborne Hydraulic System
A Test Method For the Static and Dynamic Characteristics of Servo-Motor-Pumps
Control and Influence of Valve Condition on Compression Stroke of Hydraulic Free Piston Engine
Variable-pressure Pump with Direct Drive Valve of Multi-body Spool
A Study on the Influence of Filling Rate on the Oil Leakage of Aircraft Steering Actuator
Thermal Modeling and Analysis of Oil-cooled High Speed Permanent Magnet Motor in the EHA System
Burst Analysis of the Aircraft Bootstrap Reservoir
Structure Analysis and Optimization Design of the Vx-ring
Test verification method for whole life cycle of equipment qualification test
Research on the Cavitation in the Pilot Stage of Flapper-Nozzle Hydraulic Servovalve with Fluid-Structure Interaction
Analysis of Driving Torque on Swashplate with an Additional Angle for Aeronautical Hydraulic Axial Piston Pump
Design of Electric Hydrostatic Actuator
Study on Fatigue Life of Aircraft Hydraulic Pipeline under Stress Damage of Water Hammer and Vibration
An abrasive wear model between valve plate and cylinder block in axial piston pumps
Research on Flow Characteristic for a Novel Twodimensional Two-piston Pump
Analysis of the fluid vibration transmission path of high speed and high pressure axial piston pump
Influence of Friction Term on Fluid-structure Interaction Vibration Characteristics of Pipeline
Sensitivity analysis of fluid vibration system for high speed and high pressure axial piston pump
Instantaneous Pressure in Chambers of The Novel Collaborative Rectification Structure Pump
A novel electro-hydrostatic asymmetric actuator with double displacement hydraulic pump
Performance Analysis of Mechanical Seal in Aviation Axial Piston Pump
Modeling of Degradation Process of Reciprocating Seal Based on Gaussian Copula Function
Dual valve controlled energy recovery EHA
Modeling and Simulation of a Distributed Electric Propulsion Aircraft by Modelica
Multidisciplinary Real-time Simulation System of Commercial Aircraft Hydraulic System based on AMESim and Veristand
A Sealing Performance Analysis for the Corner of a Rotary Vane Seal Based on ANSYS
A Hardware-in-the-Loop Simulation for aircraft Braking System
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- Author(s): Lei Peng ; Yu Yang ; Jiang Liting ; Zhao Xiaorui ; Sun Xuyao
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(8 pp.)
A variety of operational control methods integrated in electromechanical servo control devices are in huge demands, such as modern ships which have a high equipment vibration noise and reliability demanding and need long distance operation occasion. The electric control cabinet was designed in this paper, which integrated many operating modes such as remote-control operation, local-control operation and manual operation to control the motor-screw device precisely. It can switch operating modes at any time according to the requirements of on-site console. High reliability is also designed in this device, when one control mode fails, the other control modes can be used to control the motor. What's more, equipment vibration and noise are well considered and reduced by improving control methods. The equipment also adds relevant safety design. - Author(s): Jianying Liu ; Wenchao Hao ; Yunfu Li ; Xudong Shi ; Zhangang Yang
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(6 pp.)
In this paper, according to the quality of power supply parameters of aircraft power system and the requirement of parameter test at home and abroad, a set of aircraft power simulation experiment system is designed and developed. On the basis of NI and ADLINK hardware platform, the simulation test system uses Hall Effect sensor to collect data, builds parameter testing system based on Labview software, and completes the test of important parameters such as voltage and current, and makes fault judgment and harmonic analysis of the collected data. Finally, through the comparison and analysis of the data from the experimental platform and the theoretical value, the validity of the experimental test platform is confirmed, which provides a practical tool for the study of the parameters characteristics of the aircraft power system. - Author(s): Chen Wen-xian and Chen Zhu-ping
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(7 pp.)
This paper is mainly focused on the analysis of the transmission characteristics of the resonant WPT system to optimize the system parameters by improving the energy transfer efficiency and extending the transmission distance. Focus on improving the energy transfer efficiency and extending the transmission distance from the coil quality factor, coil structure, load selection and high frequency. - Author(s): Yinfeng Zhang ; Deyu Feng ; Hongbo Gao
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(5 pp.)
In this paper, a robust controller is proposed to overcome these disadvantages in the application of the LQG control method in the inverter, which has the disadvantage of poor anti-interference ability and robustness. This paper reveals the inner link between LQG control and robust control, and then the load and filter parameter variations acting as uncertain factors, selecting the appropriate weighting functions, a robust controller was designed by mixed sensitivity method. the whole system of simulation and experiments are verificated through the Matlab software and the production of the 10kW prototype respectively, the simulation and experimental results show that the designed robust controller using only a voltage loop can make the system has a good dynamic and static performance and robust performance, steady state voltage stability is between the 114.5V-115.5V, dynamic recovery time is in 10ms. - Author(s): Jigui Zheng ; Jing Chen ; Xibin Guo ; Yuping Huang ; Ping Zheng
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(6 pp.)
This paper designs a 6-slot/7-pole axially magnetized cylindrical permanent-magnet linear machine which is used for free-piston Stirling power generating system. The optimum structural parameters including the ratio of permanent magnet to magnetic block, the stator tooth width, and the radius of the mover are obtained for improving the back EMF waveform, reducing the harmonic distortion rate, and weakening the thrust ripple. A prototype of 6-slot/7-pole axially magnetized cylindrical permanent-magnet linear machine is manufactured and a part of performance of this machine is tested. - Author(s): Yang Zhou ; Xiaofeng Ding ; Yuezhen Liu
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(6 pp.)
Due to the inherent defects in the pneumatic and hydraulic systems, the More Electric Aircraft (MEA) has become a trend in the future development of the aircraft. With the rapid increase of the power of airborne equipment and the limit of weight and volume, the traditional silicon based power devices cannot meet the needs of MEA. Gallium nitride (GaN) power devices have become one of the most promising devices for aviation inverter power due to their advantages of high efficiency, high frequency and high power density. However, when GaN device works in high frequency, the dv/dt and di/dt slopes increased due to stray inductances and parasitic capacitances, which lead to oscillations and overshoots in gate-source voltage and affect the stability of driving circuits. Especially in aviation inverter, crosstalk between GaN power device in bridge circuits severely limits the performance of the inverter and poses a challenge to the safety of aircraft power systems. In order to solve the short-circuit of bridge arms caused by crosstalk in the aircraft power supply system, an improved design of gate driving circuit was proposed, which can eliminate the parasitic oscillation and voltage spikes, suppress crosstalk and higher order harmonics effectively. In addition, a double pulse test prototype is built and the simulation and experimental results verify the effectiveness of this drive circuit. Therefore, applying this driving circuit to the aircraft DC-DC can effectively improve the reliability and robustness of the aviation GaN inverter. - Author(s): Jiwen Han ; Dabing Zhu ; Xiting Hu ; Guang Li ; Jie Fu
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(5 pp.)
As the increasingly demand for the minimization of manipulators, a design of compact BLDC motor driver with realtime industrial Ethernet-EtherCAT interface is proposed. The essential structure of the integrated joint is depicted. This paper illustrates the constitution of the motor drive system and analyzes the designing method of motor, position sensors, controller and power device. Also, the drive control algorithm is talked about. In the experimental part, a BLDC driver within a narrow space constraint is designed. The reasonability of the hardware and software design is supported by some experiments without load in the latter part of this paper. - Author(s): Pengfei Li ; Xibin Guo ; Jing Chen ; Qing Zhao ; Zhaojing Zhang
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(4 pp.)
This paper adopts high performance current control pulse width modulation chip UC3845 as the core control part of power supply, uses double-tube parallel unit as the power part of power supply, and designs a 200W/ 24V output double-tube parallel forward-excitation type switching power supply with adjustable input voltage from 200V-1200V wide range. By analyzing the working principle and specific design method of the circuit, the problems of narrow input range, unbalanced load at feedback and system isolation are solved, and the stable 24V output is obtained. The experimental results show that the power supply has good performance. - Author(s): Li Huiyong and Cao Jiwei
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(8 pp.)
The paper presents an accurate analytical model for calculating winding inductances of permanent-magnet synchronous motor accounting for stator slots. Firstly, the vector potential distributions are obtained in each subdomain, i.e., stator slot, slot opening and air-gap (permanent magnet) by solving the governing equations with boundary and interface conditions. Particularly, the process of transforming equations into matrix format are given in detail. Then winding inductances are calculated by magnetic energy method. 2-poles/12-slots prototype machine is used for validation. The armature reaction field and inductances computed by the analytical method match the FE results very well. - Author(s): Weiwei Ye ; Ziling Nie ; Junjie Zhu ; Yi Han ; Jun Sun
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(6 pp.)
The prospects for the active neutral point clamped five-level inverter are broad in medium-voltage high-power applications. This paper has analyzed the relationship between dc-link capacitors voltage and neutral point current and then proposed a control strategy based on zero-sequence voltage injection to regulate the voltage across the dc-link capacitors. In view of an excessive fluctuation of the voltage across Flying capacitors, a more accurate control method is proposed by introducing the auxiliary modulation wave. The simulation results show that the proposed control methods are feasible and effective. - Author(s): Huang TianXiang ; Hui HuaXian ; Xue LongXian
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(5 pp.)
A simple model of more-electric aircraft (MEA) electrical power supply system has been found for testing the application of fuzzy control method in Energy Management Strategy. Parameters of fuzzy control rules are optimized by an optimization flow base on Matlab/Simulink environment. Simulation results show promising results for improving efficiency of electrical energy based on fuzzy control. - Author(s): Ting Wang ; Xiaobin Zhang ; Weilin Li ; Fei Deng
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(6 pp.)
A comprehensive model of combinable single-phase source based on SiC MOSFET for the Electrical Power System (EPS) of helicopter ground support is investigated in this paper. This model is composed of three parts which has the ability to output single-phase 115 V/400 Hz for the EPS architecture under study. The double loop control is adopted in the primary part of `the three-phase Voltage Source PWM Rectifier (VSR)'. In the second part, `Dual Active Bridge (DAB) DC-DC converter' is accomplished by phase shifting control. And `single-phase voltage source PWM inverter (VSI)' is accomplished by droop control in the tertiary part. This comprehensive model can be operated in parallel to expand the output power of single-phase AC source. Furthermore, three-phase AC source is obtained by star connection scheme of output port. The simulation results based on Matlab/Simulink show that the parallel single-phase AC source model can meet the output power requirement; more significantly, it can share the output active/reactive power quickly. In addition, the three-phase AC sources model has an ability to resist load imbalance. - Author(s): Sun Xingfa ; Nie Ziling ; Zhu Junjie ; Han Yi ; Ye Weiwei ; Sun Jun ; Wu Yanhao
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(7 pp.)
The speed sensorless control of linear motors is an important research in the field of electric drive. According to the dual-αβ mathematical model of a dual three-phase linear induction motor (LIM), this paper presents an equivalent single-αβ mathematical model and the fourth-order state equation of the dual three-phase LIM that have been derived from variable substitution for the purpose of estimating the rotor speed based on the extended kalman filter. Because the extended kalman filter algorithm is poor in estimation performance when the system state changes suddenly, a method of rotor speed estimation is proposed on the basis of suboptimal multiple fading extended kalman filter. The online adaptive regulation of the prediction error covariance matrix leads to an improvement on the algorithm for the system robustness. The use of the control strategy for a secondary magnetic field-oriented average torque current can keep the torque components of the dual three-phase currents constant and reduce the imbalance of the currents. The simulation and experimental results show that the speed sensorless control strategy is superior to the conventional extended kalman filter algorithm in the accuracy of speed estimation. - Author(s): Run Dong ; Qiaoying Zhang ; Xiaohua Wu ; Weilin Li ; Ting Wang ; Shuxian Li ; Xiaoli Duan ; Yang Yang
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(7 pp.)
More-electric aircraft is the inevitable developing trend of future. The electrical system is coupled of different areas subsystems, such as mechanical, electrical, and control etc. Multidomain simulation technology meets the demand of electrical system of the multi-domain integrated modeling. This paper has completed the modeling of multi-electric aircraft electrical system based on Dymola and FMI generalization interface protocol. According to the overall system design requirements, a cosimulation method based on FMI standard protocol interfaces is proposed, which is used to model and simulate typical constant power load. It is verified that the electrical system can be automatically distributed and reorganized under different working conditions. The high reliability design requirement of multi-electric aircraft is guaranteed. This provides important support for the research and design of multi-electric aircraft. - Author(s): Linhui Fan ; Tao Yang ; M. Rashed ; S. Bozhko
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(8 pp.)
This paper presents a sensorless control technique based on Model Reference Adaptive System (MRAS) for a symmetric dual three-phase permanent magnet synchronous machine (DTP-PMSM) whose sets of windings are spatially shifted by 60 degrees. The control design of starter/generator (S/G) system is studied. The analytical controller design is presented. The effectiveness of the controller is demonstrated from time-domain simulations. - Author(s): Dongbin Song ; Wenjiang Yang ; Yu Liu ; Yang Li ; Ying Li ; Peng Song ; Yufan Li
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(6 pp.)
The paper briefly outlines the development of superconducting materials in utility. The superconducting material manifests superconductivity, complete diamagnetism under the superconducting state. The application of the superconducting material in traditional electric machine can make it become lighter, smaller and more compact. The development of low temperature superconducting (LTS) wires and high temperature superconducting (HTS) wires applied in superconducting machine are introduced in brief. Several kinds of typical superconducting machine for airborne applications are described. A superconducting generator model is designed and the YEA simulation results in no-load and load are described. - Author(s): Xu Wenkai ; Zhu Junjie ; Nie Ziling ; Wu Yanhao ; Han Yi ; Sun Jun
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(5 pp.)
The development of the third generation wide band gap semiconductor technology contributes to the application of the full silicon carbide power module in all kinds of power electronics devices due to its advantages of high switching frequency, low switching losses and high voltage class. With the progress of more-electric-aircraft (MEA), the application of full silicon carbide power module can improve the power density and efficiency of aeronautical inverters. On the basis of the double pulse experiment, the switching characteristics of the full silicon carbide power module is compared with the traditional silicon IGBT power module, and the switching losses of the full silicon carbide power module is analyzed. An aeronautical inverter experimental platform based on the full silicon carbide power module is established. The output voltage, current, radiator temperature rise and the overall efficiency are tested and analyzed, which contributes to the promotion and application of the full silicon carbide power modules in the aeronautical inverter. - Author(s): Tongkai Cui ; Qishuang Ma ; Ping Xu ; Yuchen Wang
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(5 pp.)
This paper deals with the electromagnetic interference (EMI) suppression of SiC MOSFET by closed-loop gate drive. A closed-loop gate drive prototype is proposed to regulate the drain-source voltage to a Gaussian-shape switching waveform with infinitely differentiable orders. Tests of a chopper with inductive load are performed under closed-loop gate drive and hard switching. Switching waveforms under both cases are compared in time- and frequency-domain. Results show that the proposed controller is successfully implemented and the EMI generation is effectively suppressed. - Author(s): Ying Zhang ; Qinling Zhang ; Hao Qian ; Wenyuan Qin
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(6 pp.)
Aiming at shortcomings of pint and medium-sized unmanned aerial vehicles (UAVs) such as short flight time, low power density, low reliability and poor testability, an architecture of airborne integrated starter/generator power supply management center is proposed after demand analysis. The architecture includes engine starting, power generation, secondary power supply, uninterruptible power supply, redundancy power distribution, energy management and fault monitoring, etc. And it effectively meets the requirements of high power density, high reliability as well as high integration for airborne power supply management center. Based on the architecture displayed in part H, the available methods for starting control module, power generation module and status monitoring module are introduced in detail in next parts. And the appropriate technical route is determined through comparison, which provides technical basis for the subsequent engineering application. - Author(s): Liu Dong ; Mi Chang-bao ; Zhang Kun ; Yu Long-ji
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(7 pp.)
The interest in multi-phase (number of phase higher than three) machines for high performance applications has been growing in recent years due to their potential advantages over three-phase machines. To solve the problems of complex arithmetic in the multiphase Space Vector Pulse Width Modulation (SVPWM) control and low utilization ratio of dc bus voltage and low torque density in the multiphase Sinusoidal Pulse Width Modulation (SPWM) control, a multiphase carrier based PWM control method based on harmonics injection was analyzed. The proposed method improved the output voltage characteristic through injecting several harmonics signals to the standard sine fundamental signal. This paper, firstly, calculated the MMF distribution of a set of multiphase windings. Then, based on it, the magnetic field distribution of multiphase induction motor was discussed, and three kinds of multiphase carrier PWM technologies are compared. Theoretical analysis and experiment results show that the proposed multiphase carrier PWM method based on harmonics injection can enhance the dc bus voltage utilization ratio effectively, improve motor torque density and efficiency, while has the characteristics of low torque ripple and simple realization. - Author(s): Minghui Wang ; Yongxiang Xu ; Jibin Zou ; Hua Lan
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(5 pp.)
In order to mitigate side effects of PWM (pulse width modulation) waves in motor control system, such as bearing currents and overvoltage, LC filter can be equipped between inverter and PMSM (permanent magnet synchronous motor). However, some new issues must be paid attention when LC filter is equipped. One of them is that motor phase currents cannot be measured, so they will not be controllable. It may result in unexpected power loss. The contribution of this paper is: a sliding mode current controller for PMSM with LC filter is proposed. In order to control the current, a sliding mode controller embedded in conventional control algorithm is proposed. The state variables for motor current control are acquired by a Luenberger observer. The effectiveness is proved by simulation results. - Author(s): Haolei Chen ; Zhenyang Hao ; Chenmao Shao ; Cheng Pu ; Buqing Lu
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(7 pp.)
This paper proposes a bidirectional LLC resonant converter based on bidirectional full-bridge DC/DC converter and LLC resonant technique.And the small signal model of the converter is established using the first harmonic approximation. Since it is difficult to obtain the analytic solution of the output transfer function from the seven-order small signal model, the small signal model is reduced. The system control block diagram is established. The design procedure of the aviation 270V/28V bidirectional DC/DC is given. And a simulation model is established in MATLAB/SIMULINK to verify the correctness of the design. - Author(s): Hua Lan ; Jibin Zou ; Yongxiang Xu ; Minghui Wang ; Liang Yan
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(8 pp.)
When the lowest non-zero spatial order of the electromagnetic force is high enough in permanent magnet synchronous machines (PMSMs), the contribution of zeroth spatial-order (ZSO) radial force to the acoustic noise becomes evident. On account of this, this paper specially focuses its attention on the ZSO radial force. Finite element simulations and theoretical analyses are put to illustrate the physical essence of the force. It is found the frequency characteristics of ZSO radial force are totally the same as those of torque ripple (including cogging torque). Meanwhile, simulations show the ZSO radial force and cogging torque arrive at their local minimums simultaneously along with their low-order components under no load condition, while it is not the case under the load condition. The reason is analyzed in detail in the paper. However, when numerous flux density harmonics have been mitigated by shaping the PM arc in surface-mounted PMSMs, or the critical slot harmonics are cut down in PM-assisted synchronous reluctance machines, the relevant components of ZSO radial and torque ripple under load condition can be simultaneously largely reduced. The latter is successfully realized in an electric drive machine by the proposed method to improve the noise performance. - Author(s): Hua Lan ; Jibin Zou ; Yongxiang Xu ; Minghui Wang ; Liang Yan
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(6 pp.)
This paper deals with the improvement of low-frequency noise and vibration (NV) performance for low-speed high-torque permanent magnet synchronous machines (PMSMs). The low-frequency NV refers to that induced by the PM field harmonics and the low-frequency current harmonics, as well as their interactions. In the paper, it is proposed to weaken the effect of local force by choosing suitable pole-slot combinations firstly, and then suppress the effect of global force, i.e., torque ripple and cogging torque, by reducing the torque harmonics for further optimization. The configurations of 12-pole/18-slot and 6-pole/36-slot are finally selected. It is found a better configuration to suppress the effect of local force is usually at expense of worse torque characteristic, if the number of slots is fixed. PM shaping and step skewing are used to further reduce the torque ripple and cogging torque for both machines. In the end, the vibrations of the machines have been successfully largely suppressed, and the total sound power levels are distinctly cut down by at least 30 dBA for both machines, whether under no-load condition or rated-load condition. - Author(s): Chongwei Duan ; Hong Guo ; Xiaofeng Ding
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(5 pp.)
This paper carries out a comparison of motor loss between PMSMs driven by SiC inverter and Si inverter. Motor loss is firstly modeled. Then, a 2-D FEM analysis is conducted to compare the loss value and iron loss distribution caused by different input current waveforms provided by SiC inverter and Si inverter respectively. In order to validate the simulation result, an experiment platform is established and the comparison based on the test data is carried out with the method of 3-D efficiency map. The result exhibits that under whole operating conditions, the motor driven by SiC inverter shows an obviously lower loss than the one driven by Si inverter. Therefore, the superiority of SiC inverter on motor loss reduction is proved. - Author(s): Chen Wang ; Zhuoran Zhang ; Ye Liu ; Jianbin Han
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(6 pp.)
In this paper, the electromagnetic force characteristics of a new hybrid excited brushless aircraft generator are investigated. The big electromagnetic force can reduce the mechanical strength and the rotor reliability. In order to calculate the electromagnetic force accurately, the Maxwell stress tensor method is derived. Then the influence of field current and phase current on the electromagnetic force is researched by three-dimensional finite element analysis (3-D FEA). The optimization of the main air-gap and auxiliary air-gap length is also analyzed to reduce the electromagnetic force. Finally, both electromagnetic force and mechanical strength results show that the proposed hybrid excited brushless aircraft generator is a promising candidate for the variable frequency AC generation systems. - Author(s): G. Buticchi ; P. Wheeler ; S. Bozhko ; M. Galea ; C. Gerada
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(5 pp.)
The electrification of the transportation has shown a steady growth in the past decades. The unmistakable advantages of the electronics in terms of control capabilities, precision and the potential to reduce the pollutant emissions have been fueling this trend. The air transportation is now facing an unprecedented electrification push in the attempt to increase the aircrafts efficiency and reliability. Commercial aircrafts like the Boeing 787 and the Airbus A380 already show an overall electrical power in the MW range. In the meantime, concepts like hybrid propulsion aircrafts started to become a research reality. In this framework, the power electronics is of paramount importance to ensure an efficient and reliable power distribution and utilization. This manuscript reviews the power electronics solutions for the electrical power distribution systems. Particular attention is given to the promising technology of multiport DC/DC power converters, whose functionality is shown with a converter prototype.
An Extensible Multi Channel Servo Control Device for Marine Application
Design of Aircraft Power Failure Detection System Based on Labview
Optimization on the Transmission Distance and Efficiency of Magnetic Resonant WPT System
The relationship between robust control and LQG control And its application in the medium frequency inverter
End force analysis and optimization of an axially magnetized cylindrical permanent-magnet linear motor for free-piston Stirling power generating system
Active Gate Driver for Crosstalk Suppression of GaN Devices in Aviation bridge inverter
A Compact Motor Drive System Design for Integrated Joint of Space Manipulator
Design of a wide-range input double-tube parallel forward-excitation switching power supply
Analytical Calculation of Winding Inductances of Permanent-Magnet Synchronous Motor Accounting for Stator Slots
Capacitor Voltage Balance Control of Active Neutral Point Clamped Five-Level Inverter
Research on Energy Management Strategy for Power Supply System of More Electrical Aircraft based on Fuzzy Control Rules
Modeling and Simulation of Combinable AC Source based on SiC MOSFET
A Speed Sensorless Control Strategy for a Dual Three-Phase Linear Induction Motor Based on SMFEKF
Modeling and simulation of aircraft electrical system based on Dymola
Sensorless Control Of Dual-Three Phase PMSM Based Aircraft Electric Starter/Generator System Using Model Reference Adaptive System Method
Simulation Calculation of a Superconducting Monopolar Generator for Airborne Applications
The Research and Application of the Full Silicon Carbide Power Module in High-Power Inverter
Shaping SiC MOSFET Switching Transients by Closed-loop Gate Drive for Reduced EMI Generation
Research on Architecture of Airborne Integrated Starter/Generator Power Supply Management Center
Carrier Based PWM with Harmonics Injection for Multiphase Induction Motor Drive
Sliding Mode Controller for Current Decreasing of Permanent Magnet Synchronous Motor with LC Filter
Research on 270V/28V aviation bidirectional DC/DC converter
Characterization and Reduction of Zeroth Spatial-Order Radial Force in Permanent Magnet Synchronous Machines
Reduction of Low-Frequency Noise and Vibration for Low-Speed High-Torque Permanent Magnet Synchronous Machines
Comparison of Motor Loss between PMSMs Driven by SiC Inverter and Si Inverter
Analysis of Electromagnetic Force Characteristics of a Hybrid Excited Brushless Aircraft Generator
Multiport DC/DC Converters for the More Electric Aircraft
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- Author(s): Lv Yanping ; Wang Xiaoying ; Li Tao
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(4 pp.)
Initiated Actuator Built-In-Test is an important maintenance test for aircraft. The hydraulic system capacity shall meet the requirements of IABIT or IABIT will fail. One issue is identified when using Hydraulic-Actuation system simulation model to analyze and design the IABIT control parameters for aircraft. The issue is solved based on a lot of simulations. The IABIT design and analysis show that the system design is not isolated, combined simulation within related systems is essential and can find and solve issues in design phase. - Author(s): Zengyong An ; Yajun Yu ; Yangyang Zhang ; Mengdi Zhang
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(5 pp.)
The space position error of big angle combined motion (BACM) is large for upon platform of ball screw transmission Stewart platform (BSTSP). The kinematics simulation method is proposed for the problem above based on ADAMS software. In ADAMS software, the virtual prototype model is established, the restraints are added, the drives are set in the centre point of upon platform, the stretch length and velocity cures of six motor-driven cylinders are obtained for upon platform realizing the space position of BACM. This kinematics simulation method can solve the problem above. It improves the design efficiency and avoids the calculation error of tradition method by coordinate conversion and matrix differential, the developing cost is reduced also. The kinematics simulation method provides an optional project for designing control algorithm of BSTSP realizing the BACM. - Author(s): Bin Liu ; Qinghe Zhou ; Bang Li ; Jiakun Hu
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(5 pp.)
A batch of hydraulic actuators had an oil leakage failure. This paper introduces the sealing structure of oil seepage position and analyzes the reason of failure. After investigation, tests and comparison of the production process of the backup ring with Russian standard of the similar backup ring, we found that the size of the backup ring of the product is unstable. This paper proposes the improved measure. The test and product use demonstrate that the improved measure is effective, and the trouble of failure is eliminated completely. - Author(s): Kang Ning and Shi YouMin
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(5 pp.)
Traditional aircraft high lift system flap moves synchronously during takeoff and cruise, whose lift coefficient is a constant, which cannot make the aerodynamic load distribution and the lift optimized. So we need a technology that can adjust the lift outline of the aircraft to optimize the aerodynamic load distribution of aircraft at takeoff phase, and optimize lift and drag efficiency at cruise phase. Airbus and Boeing respectively use variable camber differential flap technology in the A350 and B787 high lift system. The technology optimizes the stress distribution on the wing and reduce the fuel consumption of aircraft. This paper is mainly about the purpose of using variable camber differential flap technology, variable camber differential unit structure, principle, installation layout and control logic. - Author(s): Jingzhong Zheng ; Jianyong Yao ; Dawei Ma
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(6 pp.)
This paper concerns high-accuracy tracking control for hydraulic actuators with unmodeled friction dynamics. Friction is a major factor that affects the performance of the servo system, and LuGre model-based friction compensation has been widely employed in sundry industrial servomechanisms. However, some parameters of this model are unknown and difficult to identify. Moreover, due to the piecewise continuous property, it is hard to be integrated with backstepping design, which needs the time derivation of the employed friction model. In this paper, a damping term is first used to counteract the uncertain nonlinear friction function and a dynamic signal is introduced to dominate the dynamic friction disturbance, then an adaptive backstepping controller is proposed for precise tracking control of hydraulic systems to handle parametric uncertainties along with unmodeled friction dynamics. The controller theoretically guarantees global bounded tracking performance via Lyapunov analysis. Finally, simulation results are given to illustrate the efficiency of the proposed approach. - Author(s): Jian Fu ; Yongling Fu ; Peng Zhang
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(6 pp.)
As the rapid growth of air traffic market in recent years, man-made CO2 emissions into the atmosphere increased largely. The economic and environment conflict need to be solved in aerospace industry. Currently, towards creating greener, safer and cheaper air transport, an interim and attractive solution is towards “More Electric” using more electric power technological advancements for non-propulsive systems in aircraft and for thrust vector control in space. The power-by-wire actuators have gained more and more attentions in nowadays electrically powered actuation systems. The innovations and developments of electrically powered actuators, for recent aircraft even for next generation of more electric aircraft and for thrust vector control system of rocket applications are presented. For safety critical actuation system like flight control, landing gear, the safety and reliability issues are of particular importance, the common redundant configurations is presented. - Author(s): Peng Zhang ; Lu Liu ; Shoujun Zhao
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(6 pp.)
For both high power and high dynamics, a dual Electro-Hydrostatic Actuator (EHA) with a peak power output of 40 kW, which was driven by two parallel monolithic Servo-Motor-Pumps (SMP), was designed, built and tested. A control strategy incorporating a non-linear PD, a notch filter and a feed forward compensation was used. Driving a heavy load with an inertia of 1000 kg.m2, the EHA has a high dynamic capacity, showing that the -3dB amplitude frequency reaches 85.4rad/s(13.6Hz) and -45° phase frequency can be as high as 25rad/s(4Hz). It is also demonstrated, compared with one with a single SMP, the duplex EHA has not only higher power output but also better dynamics since SMPs are working in linear operating ranges more time rather than approaching saturation early. - Author(s): Hao Wu ; Bo Yang ; Aping Wang ; Zhenjin Nie ; Sijia Cao
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(3 pp.)
An electric nose wheel steering system for aircrafts was introduced. For high reliability, dual identical RS422 buses are used as well as a dissimilar redundancy feedback strategy incorporating both the screw's linear displacement and the nose wheel output angular displacement. A fork-link mechanism structure is connected with the ball-screw to drive the nose wheel for both a high reduction ratio and a large torque output. A hydraulic damper is embedded in the mechanism to buffer the impact loads. Simulations and tests were finished, showing a good conformity. - Author(s): Li Huan ; Cao Lishuai ; Qin Tao
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(4 pp.)
It is difficult to predict the reliability of the actuating cylinder. Since there is a correlation between the components of the actuator, the copula function is considered to establish the dependent function between the components. In this paper , the dynamic relationship between working time and reliability is established through Copula function, at the same time, the life of the actuating cylinder is obtained. This article compares the Copula function with the completely independent and fully related conditions of each component. Furthermore, this paper proves that the Copula function can accurately predict the reliability of the actuator. - Author(s): Gang An ; Guangqiang Yin ; Renjing Liu
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(6 pp.)
The study on non-linear dynamic properties of two stage planetary gear train used in machine device with double-tooth has not been reported. This work theoretically studied the vibration model of the aircraft rotary actuator double-stage planetary gear train (Type 3K) constructed with spur gears, and used it to investigate their natural frequencies and vibration modes. The model admits three planar degrees of freedom for each of the sun, ring, carrier and planets. It includes key factors affecting planetary gear train vibration such as the time-varying mesh stiffness, integrated error of gear tooth contact, the bearing support stiffness and the other factors, and gives the vector expressions. The thesis derives the meshing pair relative displacement in the meshing line based on the analysis of planetary gear train elastic deformation, and establishes the sun, planet, carrier and ring sub-structural dynamics model by the dynamic sub-structural modeling method. For the mode, the relation between inherent frequency and vibration amplitude is investigated in detail by the dynamic characteristics analysis. In accordance with the frequencies calculated and compared with the results by using finite element method, the comparison results show that method proposed is correct. - Author(s): Liu Peng ; Li Qing ; Wang Kuo ; Zhang Yanhong
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(4 pp.)
An all-electric dual redundancy nose wheel steering servo system for unmanned aerial vehicles, including a twin-channel servo mechanism and a twin-channel servo controller, is introduced. A fault detection module and power switches in the servo controller can connect or close the main and backup channel. The system with high-reliability, quick-response, excellent motivation accuracy and easy maintenance meets the requirements of unmanned aerial vehicles, such as reliability, maintainability, safety and all electric. - Author(s): Jigen Fang ; Jinjun Wu ; Xifeng Wang ; Xiaoguang Wang ; Liang Li ; Xiang Gao ; Shuo Cheng
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(9 pp.)
A high speed on/off valve Actuator (HSVA) is a main interface between electronic control and hydraulic system for most fluid power applications such as braking systems of vehicles and aircrafts. Accurate theoretical model is the key to control the high speed on/off valve smoothly. However, modeling of a HSVA is a challenging difficulty due to the unavoidable multi-physics coupling problems in practice. For establishing mathematical model of a HSVA accurately, this study dismantles the coupling model into three interrelated sub-models, including a mechanical sub-model, an electromagnetic sub-model, and a thermal sub-model. And then, these three subsystems are modeled as a spring/mass/damper system, a nonlinear resistor/inductor system and a multi-wall heat transfer system, separately. At last, the feasibility of above three sub-models is verified by comparing the simulation results with the experimental results obtained on a test bench. Our study shows that the three subsystems are coupled to each other through resistance, displacement, and temperature. Besides, our results can be regarded as a research tool for future investigation and development of the Solenoid valves. - Author(s): Haifeng Long ; Helong Wang ; Hongbo Zhang ; Xibin Guo ; Lingyan Wang
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(5 pp.)
Electromechanical actuation system(EMAS) is widely applied in Aircraft under the background of More Electric Aircraft(MEA). A lightweight integrated four-channel electromechanical actuation system with rapid response and high power density is designed and developed according to the high level disturbance moment and limited space. The following are introduced in this paper: (1) the principle and constitution of the EMAS; (2) the design and simulation of the EMAS; (3) the experiments of the EMAS. - Author(s): Xiao Tian and Xu Xiangrong
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(3 pp.)
Aircraft Steering actuators have high static friction phenomena In recent years, which affect the use and lower reliability .in this paper, some control actuator was studied. The factors that affect the static friction of the control actuator were analyzed and feasible solutions for excessive friction of the control actuator were proposed and verified by tests. The research process and conclusion provide valuable reference for the design and troubleshooting of actuator cylinder products. - Author(s): Maokun Wang ; Le Yang ; Wenwen Qi
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(7 pp.)
This paper studies the control algorithm of the servo valve in electro-hydraulic servo system with variable pressure. The Hinf robust model is designed based on the variable parameters, and the Hinf robust adaptive controller is designed based on the Hinf robust model. The MIT adaptive control algorithm exist defect which is liable to failure due to the initial state of position-control system based on valve-controlled hydraulic cylinder. According to the defect of the MIT adaptive control algorithm, the system pressure will be measured to calculate an initial value of the MIT adaptive control algorithm. Finally, the simulation verifies that the modified Hinf robust and adaptive controller can restrain the impacts of the changes of the system parameters on the electro-hydraulic servo system. - Author(s): Xin Xie ; Chao Qi ; ShiXun Fan ; XianLiang Jiang ; DaPeng Fan
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(6 pp.)
This paper is related to the modeling and identification of precise cable drive system for acquiring tracking and pointing applications, subject to friction, mass unbalance and torque ripple. With the aim of reproducing these behaviors, a nonlinearity dynamic model is studied. The state expansion and discrete model are established. The inertia, mass unbalance, Coulomb and viscous friction are estimated through an unbiased least squares scheme. The friction model is developed by observing the disturbance torque through a state augmented Kalman filter. A sliding mode controller is designed to eliminate the torque ripple. An experimental setup is built, and the dynamic parameters are identified. The frequency response results based on the theoretical model and identified parameters provide a good interpretation with the experimental results. - Author(s): Bin Li ; Liang Yan ; Zongxia Jiao
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(5 pp.)
Self-starting capability is one of the key issues in motor design. In order to clarify this problem, this paper conducts a simulation analysis of the self-starting capability of U-shaped core motor. First of all, the cogging torque was simulated with different sizes of asymmetrical air gaps, and the initial position of the rotor was determined by using the point of zero torque. Secondly, under zero excitation, transient simulation method was adopted to make the rotor reach the equilibrium position by the cogging torque alone. These two methods are mutually verified to prepare for the next self-starting simulation. Then, under the transient simulation, the excitation is applied, and the air gap and rotor inertia are changed respectively to study their influence on the self-starting ability of the motor. The simulation results show that the asymmetrical air gap design provides the possibility of self-starting of the motor, but the self-starting ability of the motor and the asymmetrical structure and inertia are non-uniform. For a specific motor, only the air gap and inertia match each other to ensure a good self-starting capability of the motor, the matching of motor parameters is the key. - Author(s): Zhang Dandan and Tian Jun
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(3 pp.)
In this paper, a kind of hydraulic shimmy damper was designed to meet the requirements of integrating with rotary electric actuator system. Analyzes and optimizes have been done of the key parameters such as damping aperture, damping coefficient and so on. Based upon AMESim, a simulation model was established to analyze the damping coefficient and the dynamic damping of the damper by simulation. Finally, the performance of the shimmy damper was verified by the system tests. Results show that the rotary hydraulic damper is reasonable and effective and can meet the needs of engineering practice. - Author(s): Huang Ligang ; Shang YaoXing ; Jiao Zongxia ; Wu Shuai ; Li Xiaobin
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(8 pp.)
In this paper, a design method of electro-hydrostatic actuator(ERA) with four-quadrant energy regulation based on hydraulic scheme is proposed. The energy regulation module is designed in the aiding or reverse load four-quadrant condition of ERA. Then the control strategy of the new designed system is studied. By controlling the energy control module, the generator state of the motor can be shielded under aiding load operating conditions, which effectively reduces motor heating and improves the efficiency of the system. Futhermore, intensive simulation research and analysis are carried out and the results show that the effectiveness and feasibility of the based new principle system is verified and the energy.regulation can be well implemented. - Author(s): Ye Maoji and Lv Qinghua
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(5 pp.)
Structure and principle of a direct drive actuator (DDA) is studied, and based on the AMESim simulation environment, a simulation model of the DDA system is built. The simulation result of the model is analyzed theoretically and compared with the actual test data, and it shows that the model is real and reliable, its performance is satisfactory. It has assistance and guidance to the design of DDA's structural parameters and control strategy and to the simulation development of flight control system. - Author(s): Xi Xiao ; Chunqiang Liu ; Xia Wu ; Yongqing Wang
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(5 pp.)
Compared with the traditional servo valve controlled hydraulic actuator (SHA), the electromechanical actuator (EMA) has the advantages of simple structure and easy maintenance. Aiming at the load torque ripple caused by the parameter perturbation and the random change of the load in the dynamic control of the electromechanical actuator, the load torque observation method of the electromechanical actuator is carried out. According to the mathematical model of electromechanical actuator, the expression of load torque estimation is deduced, and an online estimation method is designed to observe load torque in operation process and improve torque ripple caused by parameter perturbation. - Author(s): Yanpeng Li ; Yaoxing Shang ; Zongxia Jiao
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(5 pp.)
The electro-hydrostatic actuator (EHA) is a highly integrated hydraulic actuation system, the traditional control method is difficult to achieve a good control effect in the case of highly nonlinear and external disturbances. In order to improve the control effect of EHA and improve the performance of hydraulic servo system, a SMC-Fuzzy controller is designed. The simulation results show that the SMC-Fuzzy controller has a better tracking performance than traditional PID controller, besides due to the application of Fuzzy rule, the system control input is more smooth, and reduce system chattering. - Author(s): Longfei Liu ; Yongfeng Li ; Wei Zhang
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(6 pp.)
Helicopter's active vibration control system can decrease structure vibration, increase using life and improve comfort. Based on the above advantages, active vibration control system has been widely used in lots of helicopters. One of the main parts of the active vibration control system is actuator which can generate force at given frequency and amplitude. The widely used actuator has two types, electromagnetic structure (EMS) and eccentric wheel structure (EWS). Compared with EMS which frequency is fixed, EWS's frequency and amplitude can be changed in real time and EWS has smaller volume and weight. The EWS generates force by accurate controlling four eccentric wheels' position. The command of actuator is a sinusoidal signal which frequency and amplitude is in sync with output force. Four eccentrics' position command come from this sinusoidal signal through complex algorithm. At the same time, the control algorithm control eccentric wheels' motion and insure output force doesn't change suddenly when command is changed. This paper proposes a new type of EWS, establishes its simulation model and verifies control algorithm based on Matlab/Simulink. The simulation result showed that the algorithm proposed by this paper is effective. - Author(s): Cheng Liu ; Xiaohui Sun ; Yaoxing Shang ; Zongxia Jiao
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(6 pp.)
This paper concerns the cross-linking between aircraft attitude control system and actuator, proposes a new method of designing aircraft attitude controller while considering the characteristics and constraints of actuator. The mathematical model of actuator is deduced and a servo controller is designed. Considering the characteristic and constraints of actuator, model of attitude control system is presented based on general dynamic analysis of aircraft. Under the multi-constraints of both dynamic quality and frequency domain margin, multi-objective evolutionary optimization (improved genetic algorithm) is implemented to adjust parameters of the proposed attitude controller. - Author(s): Hua Tian
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(5 pp.)
Trim computation for steady-state flight such as steady straight flight and circling is very important for Flight Control System development. A trim computation method for an aircraft, whose aerodynamic data are unknown, based on computer simulation is proposed in this paper. This trim method utilizes the principle of automatic flight control, simplifies the control structure farthest, and completes the calculation by computer simulation. It is more efficient and convenient than the conventional method of solving complicated system of nonlinear equations. - Author(s): Xiaozhe Sun ; Zhenshu Yang ; Jianzhong Yang
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(8 pp.)
Flight control Electromechanical Actuation System (EMA) has gradually been used in modern civil aircraft and has become one of the typical features of multi-electric aircraft. Since the failure mode of flight control EMA is complicated and its effect on the system is uncertain, this paper investigates the failure mechanism and failure modeling method for the typical failure modes of flight control. The effect of system design and nonlinear factors on failure characteristics can be clarified. The system architecture, fault classification and failure mechanism were firstly described. Next, the fault simulations are carried out in three different system cases, which consists of linear, nonlinear and open-closed-loop cases. Then the simulation analysis summarizes the corresponding relationships between nonlinear factors, system design and failure effects. The failure effect analysis methods can be obtained as well. In addition, the results developed in this work provide theoretical support for fault detection design, system safety-reliability enhancement and airworthiness certification. - Author(s): Jing Fang ; Xingjian Wang ; Rufei Li ; Shaoping Wang ; Weiqun Wang
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(6 pp.)
Currently, the majority of published ankle prostheses employ electrical drives or hydraulic drives. In this paper, an active ankle prosthesis powered by electrohydrostatic actuation (ERA) is proposed. ERA is a new actuator that integrates the actuation system energy source and the output actuator. It has been successfully applied to aircrafts such as the A380, A4O0M, B787 and F35. The use of ERA in the prosthesis provided high power density, and the ability to switch quickly and smoothly between passive and active modes. The prototype consists of more than ten components, such as the motor, doubleplunger pump, valves, double-outlet hydraulic cylinder, pressure sensors, accumulators, carbon fiber foot plate, etc. After rigorous verification via simulation and evaluation, this study proved that its structure was reliable and durable. A simulation model was then developed to analyze the performance of ERA, results showed that this hydraulic system could provide enough torque to satisfy energy needs of human bodies. The innovation of this study was reflected in the creative use of combining the hydraulic cylinder and the plunger pump to be a closed hydraulic circuit, thereby forming proactive assistance prosthesis. Moreover, another novelty is that micro-accumulators also used for energy storage, released when in necessity. With laboratory experiments, the overall control of the prosthesis and structural improvement are also in progress at present. - Author(s): Lingzhi Jiao ; Yaoxing Shang ; Shuai Wu ; Longxian Xue ; Xuhui Wang
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(6 pp.)
The aircraft hydraulic system is the power device in the whole machine system. The selection of which hydraulic system in the process of aircraft designing is an important issue that needs careful consideration. However, there is no systematic theory for the evaluation of hydraulic systems at home and abroad. The reason is that there are many factors that affect the energy efficiency of hydraulic systems, including reliability, weight, and cost. For multi-objective comprehensive evaluation, it is an important link to consider the influence factors of various factors on the evaluation objectives. This paper uses the means of analytic hierarchy process (AHP) and fuzzy analytic hierarchy process (FAHP) to construct the evaluation model of current airplane's hydraulic system. By comparing the results of these two models, a conclusion could be obtained that Fuzzy AHP not only has greatly distinct with the similar object, but also avoids the drawbacks that the consistency of thinking in the analytic hierarchy process is difficult to be guaranteed. - Author(s): Denghui Wu ; Yaoxing Shang ; Xiaochao Liu ; Zongxia Jiao
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(5 pp.)
At present, the traditional cabin door retractable system is designed based on peak flow and peak power. However, cabin door retractable system is turned on and off only for a very short period of time, so most energy is wasted. In order to solve the problem, a new cabin door retractable system is proposed in this paper. and the basic ideas are low-power pressurized energy storage and high-power transient operation by using the accumulator. According to this way, the installed power of the cabin door retractable system is reduced greatly and the burden on the engine is lightened at the same time. To validate the presented system, the paper establishes the simulation model of the traditional cabin door system and the new cabin door system. And the compared results show that the demand for flow and power are reduced more than 50% by using the new cabin door retractable system. - Author(s): Nan Yao ; Liang Yan ; Tianyi Wang ; Shaoping Wang
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(5 pp.)
The objective of this paper is to achieve high accuracy motion control of a novel permanent magnetic linear machine (PMLM) with hybrid three-dimensional magnet arrays. This novel PMLM was originally proposed in our preceding work. Classical PID controller is usually applied for motion control of PMLM when the relationship between driving current and output force is assumed to be linear and all nonlinearities and uncertainties are neglected. However it is unlikely to track motion accurately simply by adjusting a PID controller when there are nonlinearities and parametric uncertainties in a PMLM system like the one studied in this paper. Formulation of force coefficient in the PMLM is achieved by curve fitting based on the complex function of axial force output with respect to input driving current and displacement of movers. An adaptive robust controller (ARC) based on varying force coefficient is designed in this paper to achieve a high-accuracy tracking of motion. Results show that precise motion control of the novel PMLM with consideration of Coulomb friction, varying force coefficient and parametric uncertainties is achieved by using the ARC designed in this paper. - Author(s): Qingxin Pan ; Lei Tan ; Yaoxing Shang ; Zongxia Jiao ; Zhihui Li
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(4 pp.)
This paper puts forward the control algorithm of the Energy-Regulation Electro-Hydrostatic Actuator (ER-EHA) based on distinguishing aiding load and reverse load working condition. According to the principle of the control algorithm, during the reverse load working condition, the system is mainly controlled by the pump control system; during the aiding load working condition, the system is mainly controlled by the valve control system, and the pump control system assists in the meanwhile, by which the generator working condition of the motor is prevented. It helps reduce the energy loss and motor heating. The feasibility of this system is verified by the simulation. Compared with the EHA of fixed displacement and variable speed (EHA-FPVM), the simulation result of motor heating is reduced by nearly 35%. - Author(s): Meng Hongjun
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(5 pp.)
In this paper, aiming at the problem of the lack of output torque of the conventional two-dimensional magnetic pole array spherical actuators, the two-dimensional spatial distribution of the magnetic array of the spherical actuators is expanded into a three-dimensional space array from the perspective of the topological structure, and three-dimensional magnetic poles are innovatively proposed. The concept of an array permanent magnet ball drive is intended to effectively improve the torque performance of spherical actuators. - Author(s): Min Gu ; Shuai Wu ; Chunfang Li ; Zongxia Jiao ; Tao Yang
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(6 pp.)
The electro-hydrostatic actuator (EHA) is replacing the traditional hydraulic actuator to become an important part of the aircraft hydraulic system, because of its power by wire, easy maintenance and high reliability. But the application of EHA is limited by its disadvantage of heat dissipation. Therefore, it is necessary to establish the thermodynamic modeling and analysis of the thermal performance of EHA. In this paper, the EHA one-dimensional multi-discipline models are established by Modelica. A flexible model library of each component of EHA with thermodynamic characteristics is carried out. An EHA model based on this components are established and simulated to evaluate the correction of the model. The simulation results indicates that the models can be used to simulate the dynamic of electrical, mechanic and thermal in high accuracy. It lays a foundation for the heat control of EHA. - Author(s): Bo Yu ; Shuai Wu ; Zongxia Jiao ; Yaoxing Shang ; Yan Zhou
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(6 pp.)
High performance and high reliability actuating system is the most important airborne subsystem which is related to flight safety, maneuverability and control quality. The research of actuation system is of great significance to the sustainable development goals of large passenger aircraft and large transport aircraft. In recent years, with the development of the system and equipment in the direction of multi-function and automation, the composition of the system is becoming more and more complex. In addition to the influence of many factors such as the worse flight environment and so on, the safety research work of the multi electric aircraft becomes more important. The safety assessment has become a design analysis which must be carried out in the design process of the flight control actuating system for multi electric aircraft. In this paper, the safety evaluation of the electrical actuating system is carried out to provide a useful reference for the development of the flight control actuating system for the airliner. - Author(s): Zhen Fu ; Shaoping Wang ; Xingjian Wang
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(6 pp.)
Structured and unstructured uncertainties always exist in physical servo systems and degrade the tracking accuracy. In this paper, an effective method named adaptive robust control (ARC) with extended state observer (ESO) is compounded to control linear electric load simulator (LELS) which is an important equipment to exert aerodynamic load to flight actuation system. Adaptive robust control can solve the structed uncertainties problem and guarantee the global robustness. The extended state observer is constructed to estimate not only the unmeasured system states, but also the unstructured uncertainties (i.e., nonlinear friction, external disturbances, and unmodeled dynamics). Furthermore, the controller theoretically guarantees the performance of force tracking with a strong position coupling disturbance, which is the most essential reason for the extra force. Abundant comparative simulation results are obtained to certify the high-performance of the proposed control strategy.
Initiated Actuator Built-In-Test Analysis and Design Based On Hydraulic-Actuation System Simulation
Kinematics Simulation for Ball Screw Transmission Stewart Platform Based on ADAMS
Analysis and correction of oil leakage of a hydraulic actuator
Variable Camber Differential Flap Technology Applied in Aircraft High Lift System
Robust Adaptive Tracking Control of Hydraulic Actuators with Unmodeled Friction Dynamics
Status and Development of Electrically Powered Actuators for Aerospace Application
The Dynamics of a High Power Dual Electro-Hydrostatic Actuator
An Electric Nose Wheel Steering System for Aircrafts
Research on reliability of actuating cylinder based on Copula Model
Dynamic Model for Planetary Gear Train in a Aircraft Rotary Actuator
A Dual Redundancy Nose Wheel Steering Servo System for Unmanned Aerial Vehicles
Accurate Modeling of a High Speed on/off Valve Actuator
Research on A Lightweight Integrated Four-channel Electromechanical Actuation System
A Study on High Static Friction of Steering Actuator
Research on Robust Adaptive Control Algorithm of Position-control System based on Valve-controlled Hydraulic Cylinder with Variable Pressure
Modeling and Identification of Precise Cable Drive mechanism
Self-starting Characteristic Simulation of the U-Core Motor
Design and Verification of Rotary Hydraulic Shimmy Damper
Simulation study of EHA with four-quadrant energy regulation based on hydraulic damping valve scheme
Modeling and Simulation of a Direct Drive Actuator
Study on load torque disturbance observation and compensation in electromechanical actuator
EHA Position System Simulation Based on Fuzzy Sliding Mode Control
Research of Control Algorithm for actuator used for Helicopter's Active Vibration Control
Aircraft Attitude Control System Design Considering Actuator Based on Improved Genetic Algorithm
Trim Computation for Steady-state Flight of an Aircraft based on Simulation
Typical failure mode and effect analysis of flight control electromechanical actuation system
Active Ankle Prosthesis Powered by Electrohydrostatic Actuation Technology: Design and Implementation
Efficiency Evaluation of Current Aircraft' Hydraulic System Based on Analytic Hierarchy Process and Fuzzy Analytic Hierarchy Process
Design and Simulation of New Cabin Door Retractable System
Adaptive Robust Control Based on Varying Force Coefficient for a Novel Permanent Magnetic Linear Machine
A New Control Algorithm For Energy-Regulation Electro-Hydrostatic Actuator
The magnetic field of mathematical simulation and control method of two stators and rotors structure actuators research
Multi-discipline simulation of electro-hydrostatic Actuator with Modelica
Safety Analysis of Actuation System of More Electric Aircraft
ESO-Based Adaptive Robust Force Control of Linear Electric Load Simulator
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- Author(s): Wu Dan
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(6 pp.)
Recirculation system is an important part of the ventilation system on civil aircraft. It has a significant impact on cabin air quality. For the recirculation system, there is no airworthiness regulation in CCAR25 or quantitative requirement in authorized standards, which makes it groundless to design this system. Meanwhile, recirculation air flow rate and proportion vary greatly on different types of aircraft. Therefore, a thorough investigation into the design philosophy of recirculation system is deeply needed. This thesis looks into the interrelationship between recirculation system and cabin air quality parameters, and develops a design method for recirculation system from the perspective of cabin air requirements. By applying this method to certain type of aircraft, it is proved to be feasible and effective to find an appropriate proportion of recirculated air, which lays a solid foundation for system design. - Author(s): Xuede Sun ; Yudi Liu ; Guopeng Nan
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(3 pp.)
Thanks to low noise requirements on commercial transportation aircraft and numerical simulation which helps acoustic engineers more deeply understand noise source and propagation mechanism, OEM invests more money on commercial software and acoustic research projects. This paper describes a joint research project on noise of aircraft Environment Control System (ECS), invested by Shanghai Aircraft Design and Research Institute (SADRI) of Commercial Aircraft Corporation of China (COMAC). In this paper, ECS noise propagation mechanism is studied which can explain how the noise is propagated from the source to the receiver. Based on the research results, the possibility of numerical modelling application on ECS ramp noise is discussed, and a fast engineering method is proposed for predicting aircraft ECS noise and risk control. - Author(s): Chao He ; Ying Zhou ; Gao Li ; Wenjing Ding ; Ang Li
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(5 pp.)
In order to study the environment temperature control method in the low pressure chamber, the numerical simulation and tests were conducted. The heat transfer process in the low pressure chamber was simulated by Fluent, and the radiation and heat conduction were considered to research the effect of the shroud opening hole, then the forced-convection was added to the simulation to research the effect of the forced-convection fan. No-load and on-load tests in the low pressure chamber were completed to research the effect of the test pressure, and the test pieces and toolings. The results show that, the shroud opening hole could make the uniformity of environment temperature worse, and the forced-convection fan being rationally designed could improve the characteristic of environment temperature, and the test pressure, the test pieces and toolings could affect the environment temperature. The environment temperature control method in the low pressure chamber should take all these factors into account, and can be applied to the development of the near space environment simulation equipment. - Author(s): Lan Ma ; Yanna Li ; Shehong Qi
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(6 pp.)
The 65# coolant is generally employed in aircraft liquid cooling system (LCS). However, the obvious rising viscosity of 65# coolant when temperature drops below -40Y always results in some troubles to liquid pump, such as difficulty start up and poor reliability[l]. The exhaust hot air which is discharged from precooler can be applied to heat LCS pipe with advantage of decreasing aircraft performance penalty because of integrated energy management. In this paper, the heat-transfer characteristics of LCS pipe surface is researched seriously and the dynamic simulation of heating performance of hot air for LCS pipe is calculated as well. Two results can be obtained as follows: While mass flow rate of hot air is stable, the heating time is directly proportional to pipe length; While the pipe length is stable, heating time will decrease when the mass flow rate of hot air increases. - Author(s): Zhao Miao and Pang Liping
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(4 pp.)
With the increasing power of airborne equipment, the airborne thermal management technology has been paid more and more attention. Because of its high COP value and high refrigeration capacity, vapor cycle cooling occupies an important position in active thermal management technology. This article mainly calculated vapor cycle cooling system as a model. Evaporator, condenser, compressor, electronic expansion valve and flight environment model are set up in AMEsim software. A dual control strategy is established to meet the requirements of external complex flight conditions by using the supercooling of condenser and the superheat of evaporator outlet as the objective function. Based on the change of the power demand of typical flight envelope and electronic equipment of a certain type of aircraft, the dynamic performance simulation study of the airborne vapor refrigeration cycle was carried out. The dynamic simulation results can provides guide for designing the airborne vapor cooling cycle. - Author(s): Xie Fei and Pang Liping
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(4 pp.)
With the improvement of comfort requirements about transportation vehicle, operation stability of vehicle air conditioning system can not be ignored. Compact design, high efficiency and enough refrigeration capacity become the optimization objective of vehicle air conditioning system. A vehicle air conditioning system, including the main simulation model such as compressor, condenser, evaporator and throttle, was built by AMESim in this paper. It carried out simulation analysis of compressor operation. What's more, the influence of the variation of inlet air parameters on refrigeration performance was studied, which verified the reliability of the system performance. - Author(s): Tang Huiru and Wang Xuyang
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(4 pp.)
This paper studies about verifying the cabin temperature compliance in the case of aircraft ETOPS flight with cold day emergency ventilation. During ETOPS flight in cold day, due to its simple control logic, emergency ventilation will lead to too low cabin temperature and cause unrecoverable damage to the human body. Based on the premise, this paper puts forward a method of intermittent closing the emergency ram air door to keep the cabin warm. To confirm the feasibility of the method, this paper conducts numerical simulation for a certain type of aircraft in MATLAB, which can be used to judge whether the temperature environment is harmful to human body according to the method IREQ in ISO11079. The calculation result shows that by opening and closing the emergency ram air door twice among 135min ETOPS flight can ensure the cabin temperature within the acceptable range, and meet the requirement of ISO11079 about the human body tolerance time in cold environment. - Author(s): Peng Xiaotian ; Liu Weihua ; Li Chaoyue ; Feng Shiyu
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(6 pp.)
Firstly, the necessity of adding a refrigeration system to a helicopter is described. It is considered that the vapor cycle refrigeration system is the development trend of the future airborne refrigeration system. Taking the AC313 helicopter as the research object, this paper using Airpak software and kepsilon double equation turbulence model, the simulation results of cabin temperature field, velocity field, PMV-PPD and air age distribution are obtained. The comparison and analysis of the simulation results of the two schemes show that the side air supply is more comfortable for passenger than the downward air supply under the same condition. - Author(s): Gang Fan ; Fei Wang ; Jun Guo ; Chengyan Liu ; Weishi Deng ; Yunfeng Zhao
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(5 pp.)
Compressor is the key equipment of the on-board evaporation cycle system. A complete aerodynamic design method of refrigeration centrifugal compressor is developed in this paper. The method is divided into two parts, which are used to design and analyze separately. Based on the method, a two-stage centrifugal compressor with airfoil diffuser is designed and its performance is predicted. The design rotation rate and pressure ratio are 70000rpm and 4.3 separately. 3D CFD simulation results show that the compressor can meet requirements of the design point of aircraft evaporative refrigeration cycle system. - Author(s): Gan Jun-Jie ; Xu Xing-xin ; Hu Jin-hai ; Xu Jun ; Han Zi-Qiang
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(4 pp.)
Oxygen regulator is the important component of oxygen-supply system. Experiences shown that when the oxygen regulator worked, the pressure of breathing gas through mask would be lost. The gas pressure value in the mask cavity would be lower than the set value of the pressure system. The pressure may cause some problems such as pressure drop as well. As the typical ergonomics problem of aircraft oxygen-supply system, the working-effectiveness of pilots could be influenced by the pressure loss. A series of studies shown that the design of ejector structure was the effective method to solve the problem. The reasonable turbulence model should be established so as to design a reasonable ejector structure. The paper quantified the various turbulence models of the ejector through numerical simulation, and the data shown that compared with the test results, the results of SST model was the closest. In summary, the SST model could effectively simulate the internal flow of the ejector and the numerical results of SST model were significantly better than other models. The research of this paper could make contributions to the design of the ejector. - Author(s): Wang Wei and Yao Xiangru
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(7 pp.)
There will be a lot of fog or condensate water in the cabin when the military or civilian aircraft is skiing on the ground or flying at low altitude in a high-temperature and high-humidity environment, which has a great impact on the performance of electronic equipment, refrigeration system, and effective commercial loading. In order to explore solutions to the cabin condensate water, three-wheel bootstrap-cycle refrigeration system with a high-pressure water separator is taken as an example to analyze the the change of humidity ratio and condensate in moist air at each state point of the refrigeration system , as well as the relationship between the reduced cooling capacity of the cold air and humidity ratio at the inlet of the refrigeration system. By combining with the experimental results of an aircraft refrigeration system and solutions for condensate water in the cabin, some measures are proposed to effectively solve the cabin condensate problem : a) installing a low-pressure water separator, b) installing a diffuser pipe water separator respectively after the secondary radiator and reheater, c) reasonable designing and matching of cold air ducts, and d) installing the drainage device at the low point of the pipeline of cabin air distribution system. - Author(s): Zheng Wenyuan and Zhan Hongbo
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(5 pp.)
The paper puts forward the concept of maximum available enthalpy of heat exchanger. The maximum heat exchange capacity of heat exchanger depends on the smaller one of the maximum available enthalpy values of the cold and hot fluids. Based on the concept, the expression of enthalpy efficiency of heat exchanger and the method of calculating the enthalpy efficiency of heat exchanger without phase change and wet heat exchanger are defined. Experimental results show that there are no obvious difference between temperature difference parameter and enthalpy efficiency under the condition of low moisture content and enthalpy efficiency can reflect the heat transfer performance of wet heat exchanger more visually and faithfully. - Author(s): Lu Yuliang
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(5 pp.)
This paper takes a type of aviation turbine cooler as the research object, and An aviation turbine cooler running state monitoring system covering all the operating conditions is established. The test system provides the product's vibration magnitude under different operating conditions by means of an acceleration sensor sticking to the product, then it can determine the health status of the product in operation by monitoring the spectral acceleration value. The critical speed of the rotor system of the aviation turbine cooler can be obtained accurately through the test system. According to the test results, the finite element mode of turbine cooler's rotor will be modified, to ensure that the FEM-calculated values are in good agreement with the test-measured values. - Author(s): Qihang Lu ; Dalin Zhang ; Shuquang Xiao
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(5 pp.)
According to the mission profile of a certain aircraft, a developed environmental control system driven by power turbine is proposed and system bleed air flow demand and output power of the power turbine were calculated. Then, power turbine output power is calculated using fluent numerical simulation in case of different flight altitudes. The results of supply and demand indicate that power turbine can provide enough power to ensure the normal operation of the system, and is superior to the existing high-pressure dewater system. - Author(s): Meng Fanxin ; Gao Zanjun ; Zheng Wenyuan ; Hu Wenchao
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(5 pp.)
The features of economy and environmental protection about civil aircraft are introduced. The development direction of airborne electromechanical system is pointed out on more electrical aircraft. The technological advantages and development status of electrical environmental control system are analyzed. The key technologies of electrical cabin supply air system are described, including high pressure ratio compression, centrifugal compressor anti-surge, variable diffuser design, air bearing supporting, large power motor control, high speed rotor cooling, foreign object damage protection, air inlet anti-icing. It is very helpful to provide technical support for environmental control system development for new generation green civil aircraft. - Author(s): Lu Jun and Zheng Wenyuan
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(5 pp.)
A tube-intensive heat exchanger is intended to be used as precooler in strongly precooled aircraft engine. In the heat exchanger, supercritical helium is used as the cooling medium. In the present study, the flow of supercritical helium in the capillary tube in the case of high heat flux was modeled. The simulation results show that the physical property of the supercritical helium flow in the capillary tube are significantly changed; the pressure drop of the supercritical helium flow in the capillary tube is considerable and it is favorable to reduce the pressure drop by increasing the pressure of the fluid; the benefit of heat transfer enhancement incurred by the inside diameter reduction under low heat flux is lower than the cost of the pressure drop; but the benefit of the heat transfer enhancement incurred by the inside diameter reduction under high heat flux is higher than the cost of the pressure drop. The study serves as a basic reference for research on strong precooling technology. - Author(s): Xue Xiaoyan and Ke Peng
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(6 pp.)
In order to solve the minimal cut set problem of “Unexpected pressure loss inside the cabin under normal operating conditions” in cabin pressure control system, this paper aims to apply the MBSA (Model Based Safety Analysis) method to PSSA (Preliminary System Safety Assessment) of cabin pressure control system instead of the traditional safety analysis method. The components' failure mode models are established based on the finite-state machine theory using graphical development tool Stateflow according to the function block element of each component. The failure propagation model(FPM) which combined the normal state and failure state of system is carried out by adding these failure mode models into system nominal model. Eventually, the minimal fault cut set of “Unexpected pressure loss inside the cabin under normal operating conditions” could be generated according to the FPM. The main objectives of the study are to improve the reliability of cabin pressure control system and provide safety requirement reference at the early design stage. - Author(s): Xiaoming Wang ; Sujun Dong ; Zheng Liu ; Aicheng Li ; Fanxin Meng
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(5 pp.)
As the aeronautical armament is developing to the direction of faster speed, higher stealth and equipped with high-energy weapons, the heat sink design of the airborne environmental control and thermal management system (ECTMS) faces great challenges. Based on practical applications, the integrated design idea and three novel integration schemes that combine the heat release of the ECTMS respectively with the engine inlet, the engine bypass and the fuselage skin are proposed, as well as their detailed structure and manufacturing technology. These integration schemes not only avoid using ram air, but also meet the high demand for huge heat release and ensure the aircraft's overall performance reach the international advanced level. - Author(s): Yu Xu ; Guohua Li ; Weiwei Chen
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(4 pp.)
Two-dimensional numerical investigations of flow boiling of R134a in micro-channels during maneuvering flight with hypergravity levels of 1-15 g and directions of 0°-180° were conducted. Flow patterns, temperature and pressure fields of the simulation domain are obtained, and the effects of hypergravity on flow boiling characteristics are analyzed. The results indicate that the flow boiling characteristics during maneuvering flight are significantly different from those on ground. When the hypergravity has the same direction as the flow (thetas = 0°), the heat transfer coefficient remains basically invariable, while the frictional pressure drop decreases. When the hypergravity is perpendicular to the flow (thetas = 90°), the heat transfer coefficient decreases with the increasing hypergravity and the frictional pressure drop decreases slightly. When the hypergravity has the opposite direction with the flow (thetas = 180°), the heat transfer coefficient keeps almost unchanged, while the frictional pressure drop increases. Since the flow evolves into a quasi-stratified flow at thetas = 90°, the heat transfer deterioration occurs due to dryout. - Author(s): Wang Ning ; Chen Weijian ; Ning Guoli ; Ma Hui
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(6 pp.)
In this paper, the three-dimensional numerical simulation of solid-liquid two-phase flow in a vortex oil filter is performed by means of numerical simulation. The Reynolds stress turbulence model is used in the simulation flow field, and the DPM model is used for solid particle tracking. The influence of key structural parameters and operating parameters on the filtering effect was mainly studied, such as the inlet width, the size of the overflow pipe, the wall thickness and the insertion depth, the size of the cone angle and the length of the cone end. The results provide the basis for the rational design of the vortex oil filter. - Author(s): Wang Siqi ; Chen Wei Jian ; Chen Liuzhong
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(6 pp.)
Based on the simplified airborne integrated thermal management system, this paper aims to study the dynamic characteristics of the system under the action of disturbance and provide theoretical basis for the study of system control scheme. This paper uses MATLAB/SIMULINK platform to develop Unmanned Aerial Vehicle (UAV) fuel system simulation model library. On the basis of the fuel of a certain UAV thermal management system, the simulation model is built and the simulation calculation of dynamic performance is carried on. Fuel temperature and the electronic equipment heat load is studied on the impact of change on system disturbance characteristics, and the control strategy of general application is put forward. - Author(s): Li chaofei ; Chen weijian ; Huang zhengshi
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(6 pp.)
A large amount of gases need to be introduced into the aircraft Environmental Control System (ECS) from the engine compressor during flight. The gases at high temperature and pressure usually contain lots of dust particles which should be removed. The cyclone dust collector involved in this paper is a new type of "no sieve" dust collector which could proudce rotational flow with staionary guid vane. Depending on its unique structure, the cyclone dust collector can separate dust particles from airflow due to the density defference between them. Its own geometric parameters have great influence on the dust removal performance. With numerical simultion method, this article analyzes the influence of the guide vane, collection cavity and separate channel on the dust removal efficiency and flow resistance, which plays a very important role in structural design of dust collector for bleed air system of ECS. - Author(s): Song Kai ; Chen Weijian ; Zhang Xuyan ; Shen Hao
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(6 pp.)
Aircraft has become the main means of transport for people to travel. In this case, the thermal comfort and thermal safety of the human body in confined space receive more and more attention than before. At present, most studies of the thermal comfort only consider surface temperature of human skin. From the perspective of the core temperature of the human body, the thermal comfort and thermal safety of the confined space are discussed in this paper. Based on JOS-2 (Jointed Circulation System-2) model, the temperature and velocity distribution in the cabin of aircraft are obtained under different wind parameters through the numerical simulation. Then the thermal comfort of the cabin is analyzed and the research in this paper has higher application vale in engineering. - Author(s): Huanfa Wang ; Guiping Lin ; Xiaobin Shen ; Lizhan Bai ; Rui Yang ; Bing Sun
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(5 pp.)
This work investigated the startup performance of a loop heat pipe (LHP) with non-condensable gas (NCG) under different evaporator tilt angles from -15° to 90°. The working fluid of the tested LHP was ammonia and nitrogen was injected into the LHP to simulate NCG. The main conclusions are summarized as follows: (1) When the tilt angle of evaporator was relatively small, the LHP could operate normally unless there was a large amount of NCG. The reverse flow usual occurred in the case without NCG and could be inhibited in the case with a small amount of NCG; (2) When the tilt angle was relatively large, the LHP could startup successfully with a small amount of NCG but not without NCG. (3) The LHP could not startup when the NCG inventory was large enough at all evaporator tilts. - Author(s): Xue Yang ; Guiping Lin ; Yu Zeng ; Zuodong Mu ; Bing Sun
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(5 pp.)
The comprehensive performance test of the environmental control cabin requires the insulation of the system. It is of great significance to analyze composition of thermal resistance and control the heat leakage performance of the environmental control cabin. Based on the simulation and experiments, temperature distribution of the core cabin section was obtained in two methods, which results were analyzed in details. Through the comparison and analysis, heat leakage of the environmental control cabin was given in the design situation. - Author(s): Qi Yang ; Yanpei Huang ; Jingquan Zhao ; Kan Xu
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(5 pp.)
With the rapid development of microelectronic technology, airborne electronic equipment is developing towards high performance, high power and miniaturization. High-heat-consumption chips pose a new demand for heat dissipation. Micro-channel evaporator and low-temperature brazing technology provide a new solution for this demand. Through experiments and numerical calculations, the effects of microchannel structure and boiling characteristic parameter on heat transfer performance are analyzed. Results show that the microchannel is capable of reducing heat transfer temperature difference by 18%, and large aspect ratio can improve heat transfer performance of micro-channel evaporator. Braze welding interface can obtain high interfacial heat transfer coefficient, with overall heat transfer coefficient up to 3~4 W/cm2K. - Author(s): Yongbo Tao ; Lizhan Bai ; Yuandong Guo ; Guiping Lin ; Jiang He ; Jianyin Miao ; Hongxing Zhang
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(4 pp.)
A cryogenic loop heat pipe (CLHP) is an efficient two-phase heat transfer device. It works without mechanical moving parts, external power, vibrations and electromagnetic interference. Hence, the CLHP can isolate optics and detectors from mechanical vibrations and improve image quality of large Far Infrared space telescopes. In this experiment, the working fluid was nitrogen and the operating temperature range was 80120K. The method of supercritical startup was by applying capillary pump with power. In this paper, the effects of different capillary pump powers on supercritical startup characteristics, relationship between charge pressure and heat transfer limit were studied. In the end, the responsiveness and temperature stability with heat load changing cyclically were investigated. The CLHP could achieve successful startup under auxiliary heat load of 2W and got a heat transport capacity of 3W. - Author(s): Yu Zhou Zhong ; Jing Quan Zhao ; Yi Zhang
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(4 pp.)
This paper proposed an engineering calculation method for infrared radiation characteristics of aircraft environmental control system exhaust. The study was based on computational fluid dynamics (CFD) and the fundamental theory of radiative transfer. First, the temperature filed of the environmental control system exhaust was simulated by CFD model. The obtained temperature filed was then divided into a quantity of layers with the same temperature and pressure from inside to outside. Subsequently, the infrared intensity of the carbon dioxide and vapor in the exhaust of each layers was calculated respectively. From accumulating the calculated infrared intensity of each layer, the total infrared intensity of the environmental control system exhaust was obtained in presence of the radiant energy attenuation. Finally, the infrared intensity in 3~5 μm and 8~14 μm bands along with the detection angles was depicted and analyzed. - Author(s): RuiJie Wang ; JingQuan Zhao ; Lei Zhu ; DongHai Zhang ; GuoHua Kuang
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(7 pp.)
Low-grade waste heat resource in industry cannot be effectively recovered which is a significant composition of industrial waste heat. Organic Rankine Cycle (ORC) has been turned out to be a desirable solution due to its unique thermodynamic performance. On the basis of the thermodynamic and mathematical models established in the paper, effects of evaporation temperature, pinch point temperature difference in evaporator, degree of superheat, condensation temperature and degree of supercooling under different conditions for various working fluids including isentropic and dry fluids on net power output, thermal efficiency as well as exergy efficiency are investigated. In the process of modeling, mechanical efficiency of turbine and pump are both taken into consideration and irreversibility of the ORC system are expressed in novel form. Results reveal that evaporation temperature and condensation temperature has an obvious impact on system properties, and degree of superheat is not necessary to obtain higher efficiency when isentropic or dry cryogens are chosen. - Author(s): Zheng Liu ; Sujun Dong ; Hongsheng Jiang ; Aicheng Li ; Fanxin Meng
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(6 pp.)
Based on the simulation data of performance of centrifugal compressor, this study analyzed the flow rate and efficiency curve of the compressor. By using third-order polynomial fitting method, we compared different results and found that the optimal sampling method was to have 5 lines of rotating speed with 7 different flow rate points in each line, in total 35 sample points, which satisfied the 5% fitting accuracy with minimal sample point and minimal experimental cost. Typical sample points for this optimal method was to set 3 lines of rotating speed and 3 flow rate points to be the maximum (rotating speed) flow rate, minimal (rotating speed) flow rate and the designed (rotating speed) flow rate, respectively. The rest sample points were distributed among those typical sample points. Finally, this sampling method was validated by the experimental results of centrifugal compressor. - Author(s): Lu Jun and Zheng Wenyuan
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(5 pp.)
Tube-intensive heat exchanger, which consists of capillary tubes, can serve as the precooler used by strongly precooled aircraft engines. In the present study, the flow and heat transfer of air-swept capillary tube bundle was modeled. According to the simulation results, the Nusselt number (Nu) is mainly related to the Reynolds number (Re), the influence of the tube diameter, transverse tube spacing and longitudinal tube spacing on Nu are not significant, the transverse tube spacing is favorable to achieve reduction in pressure drop, and the longitudinal tube spacing has a very slight impact on the pressure drop. Therefore, a compact tube bundle structure with small pressure drop can be obtained through appropriately increasing the transverse tube spacing and decreasing the longitudinal tube spacing. This study is aimed at providing a foundation for research on strong precooling technologies.
Design Method of the Recirculation System Based on Cabin Air Requirements
Modeling for Commercial Aircraft Environment Control System Ramp Noise
The environment temperature control method in the low pressure chamber
Heating performance simulation of double-wall pipe for aircraft liquid cooling system
Dynamic Numerical Investigation Of Airborne Vapor Cycle Cooling System
Research on Performance Simulation of Vehicle Air Conditioning System
The verification of cabin temperature compliance in the case of aircraft ETOPS flight with cold day emergency ventilation
Air Flow Organization Simulation of AC313 Cabin Air Conditioning Based on Airpak
Design and Analysis of a High-speed Centrifugal Refrigerant Compressor
The quantified research of the turbulence model of ejector based on CFD
Research on the Relationship between Humidity and Performance of Air Cycle Refrigeration System
Study on Enthalpy Efficiency of Wet Heat Exchanger
Test and Analysis of Dynamic Characteristics of Some Aviation Turbine Cooler's Rotor System
Performance analysis of the power turbine in a environmental control system
Research of Key Technologies for the More Electrical Aircraft Electric Cabin Supply Air System
CFD Modeling of Flow and Heat Transfer of Supercritical Helium in Capillary Tube
PSSA of Cabin Pressure Control System Based on Finite-State Machine Model
Integration Schemes for Heat Sink of the Airborne Environmental Control and Thermal Management System
Numerical simulation of flow boiling in microchannels during maneuvering flight
Numerical investigation of influence of structure and operating parameters on performance of vortex oil filter
Analysis of Disturbance Characteristics of UAV Fuel Thermal Management System
Influence of Geometrical Parameters on Dust Removal Performance of Cyclone Dust Collector for Bleed Air System of ECS
Thermal Comfort Study in Aircraft Cabin Based on Human Thermal Regulation Model
Effect of evaporator tilt on the startup performance of loop heat pipe with non-condensable gas
Analysis of Heat Leakage in the Environmental Control Cabin
Analysis of micro-channel flow boiling thermodynamic characteristics
Experimental Study of a Nitrogen Loop Heat Pipe for Cooling Large Area Heat Source
Calculation of Infrared Radiation Characteristics of Aircraft Environmental Control System Exhaust
Performance Analysis of Organic Rankine Cycle for Low-Grade Waste Heat Recovery in Industry
Study on Sampling Method for Performance Curve of Centrifugal Compressor
Numerical Simulation Study on Air-swept Capillary Tube Bundle
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- Author(s): Langlang Cui ; Zhineng Zhu ; Fahua Ge ; Qiang Chen ; Hongshun Shi
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(5 pp.)
The contact friction damper is still used in the throttle control device of the fighter, the performance of its contact-sensitive component is easily affected by the airborne environment that may be causing serious hazards to the safety of flight. A non-contact permanent magnet hysteresis damping motor is presented in this paper, the operation principle and the basic structure are introduced, the magnetic performance, mechanical vibration property and the thermal distribution are also studied. A prototype is manufactured and tested, the results show that the design objectives were well satisfied. - Author(s): Wu Ming ; Wu Liang ; Tan Shuai ; Jin Lou
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(7 pp.)
Aiming at the optimization of the kinematic parameters of an advanced ejection seat, the dynamic characteristics, control characteristics, control methods, optimization methods and robustness of the ejection seat have been discussed and analyzed in the paper. In addition, the related key technical problems have also been explained to determine the research programs and technical approaches. All of the above have provided a practical and feasible method for the optimized simulation of kinematic parameters of the ejection seat, and pointed out the direction of improving the life-saving performance of the seat, which will contribute a great value in engineering applications. - Author(s): Tingwei Zhong and Tianju Shen
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(4 pp.)
With the rapid development of the helicopter industry and more and more frequent marine activities, the urgent need for flight safety and emergency rescue is submitted. When a helicopter break down, the Emergency Flotation System (EFS) is generally started in the air. As the pilot lost consciousness, tension or other unexpected factors failed to open the buoy in time, causing failure of lifesaving. The automatic start technology can automatically output the starting signal according to the detection signal and logical judgment. It prevents the helicopter from sinking and overturning and significantly improves the flight performance and safety. This paper describes the automated water-landing monitoring technology of helicopter, analyzes the principle of water-landing sensor, and puts forward a safe and reliable water-landing determination method. Then the water-landing controller is designed, and the maintenance and detection circuit of the ignition switch is analyzed. The experimental results demonstrate that these techniques are feasible. - Author(s): Wujun Xie and Liwu Min
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(4 pp.)
The delethalization test equipment can be used to assess the possibility of occupant's injury caused by civil aviation seat in emergency landing, A Hybrid ,, ATD head/neck assembled with a triaxial accelerometer in the ATD head is accelerated by a cylinder to impact test piece, to study occupant's injury mechanisms, including blunt trauma injuries caused by the crash loads, and additional injuries caused by sharp or injurious edges or features during the evacuation. This essay aims to design a high-speed cylinder with a buffer piston to achieve high impact speed with low pressure, a coaxial rotating pivot arm and push arm to prevent ATD neck from bending and twisting before the impact, an automatic brake to avoid ATD head multiple impact test pieces, and two devices with high precision encoder and photoelectric sensor to measure the impact speed. The test results show that the ATD head/neck assembly can impact the test piece at less than 10.36m/s, and the delethalization test equipment completely meets the standard requirements. - Author(s): Chuan Chen ; Bo Yang ; Hao Wang ; Haoyuan Wang
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(4 pp.)
Based on aircraft attitude sensor information, a series of possible aircraft attitude combinations are obtained using the attitude-prediction algorithm based on fixed-step integration. Submit the data to the safe escape envelop model obtained by interpolation of the ejection seat performance parameters to evaluate the safety performance of the seat ejection in all possible predicted postures. If there is a possible posture that does not meet the ejection safety performance, the safe escape envelop predict is performed in the form of the remaining time from the unsafe ejection attitude. The method provides realtime prediction of safe escape before the attitude of the aircraft exceeds the escape envelop, so as to avoid the accidental ejection failure caused by the pilot's misjudgment of ejection timing. - Author(s): Zhu Bin ; Ke Peng ; Li Minggao
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(6 pp.)
In order to evaluate the differences in the restraint performance of seat belts on different percentiles dummies and compare the effects of the safe belts locking parameter on the performance of the restraint, a dynamic model of dummy-beltseat system is established. With the acceleration curve at seat base during typical arrested landing reported in the literature as the input, numerical simulation was conducted to test the validity of the model. The head displacement, the angle between trunk and seat-back of dummies and head displacement differences under different locking parameters during arrested landing are obtained. The results show that the head displacement of 50 percentile Hybrid III dummy is the smallest, about 0.25m(forward) and 0.15m(vertical), the angle between trunk and seat-back is about 20°. And the head displacement when belt locked reduces with the locking time shorten, about 66% for 5 percentile dummy and 23% for 95 percentile dummy when the locking time change from 0.5 to 0.2s. However, for 95 percentile dummy, the head displacement after the locking device releasing when 0.2s is bigger than when 0.35s. As for the injury, dummy has a relative worse situation when the locking time is 0.35s than other conditions. The paper reaches the conclusion that this model has the best restraint performance on medium-sized body, and shorten the locking time can improve the restraint performance to a certain extent for sure but for large-sized body, the restraint performance is not good if the locking time is too short. There is a balance point to ensure the best effect combining the displacement before and after the belt releasing. As for injury, due to the small acceleration in this process, the risk of injury is relatively small and the influence of locking parameter is also small. - Author(s): Dong Lingfei and Ke Peng
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(6 pp.)
CCAR 25.803 shows detailed airworthiness requirements for the emergency evacuation of civil aircraft. Compliance demonstration for airworthiness must be based on simulation tests, but the analysis method is a powerful tool for the design of emergency evacuation systems. This paper establishes a new mathematical model of emergency evacuation process, develops a calculation program and proposes a simplified analysis method for calculating possible evacuation time. Typical features include 1) a two-dimensional matrix description method for cabin layout; 2) Random set of personnel attributes based on airworthiness requirements; 3) Dynamic adjustment of door usage efficiency. The simulation of emergency evacuation procedure for AIRBUS 320 and BOEING 767 was compared with literature experimental data and commercial software Pathfinder's results to show the correctness of the analysis method in this paper. This analysis method can quickly optimize the design of the emergency evacuation system and evaluate the evacuation time under the premise of ensuring accuracy. It can also provide assistance for aircraft cabin layout design and airworthiness verification. - Author(s): Fang Di
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(4 pp.)
This paper illustrate the necessity for Tire Burst particular risk safety analysis, and propose the basic method and detail for analysis, based on airworthiness provisions and ARP 4761, that will have directive significance for PRA work of civil aircraft. - Author(s): Lanhui Liu ; Rudong Tian ; Fei Gao ; Qilong Liu
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(5 pp.)
Emergency Evacuation Slides for commercial aircraft have been addressed to ensure the safety for passengers due to emergency landing and ditching, which provide the rapid deployment, evacuation safety, floatation stability for the safe and orderly evacuation out of the cabin. The simulation improves the reliability of beam strength and evacuation rate; and, prototype test results show that the escape slides can satisfy the priority-based requirements. - Author(s): Yang Bo ; Diao Xungang ; Huang Jun
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(6 pp.)
The new generation stealth fighter adopted an integrated canopy structure, which has large size and heavy weight. In this paper, the theoretical mechanics method was used to calculate and analyze the dynamic mechanical properties of the rotation-opening system and the front-rocket jettison system. The emphasis is the optimization of the rocket thrust performance and the opening stability under various wind loads. The calculation method can be used as a supplement to dynamics or fluid simulation software (ADAMS, CFD, etc.). Especially in the preliminary design phase, the canopy system can be optimized rapidly.
Design of High Reliability Hysteresis Damping Motor with Adjustable Torque for Fighter
Research on the Optimized Simulation of the Kinematic Parameters of an Advanced Ejection Seat
Research on helicopter water-landing monitoring technology
Design of delethalization test equipment for civil aviation seat
Safe Escape Envelop Predict method based on seat performance and attitude prediction
Evaluation the performance of a typical seat belt restraint system for carrier-based aircraft during arrested landing process
Development and Verification of the Simplified Analysis Method to calculate the Emergency Evacuation Time for Civil Aircraft
Particular Risk Analysis Method of Tire Burst for Civil Aircraft Flight Control System
Reviews of Emergency Evacuation Slides for Commercial Aircraft
Calculation Analysis on Dynamics of Integrated Canopy System
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- Author(s): Zhang Qian and Wang Lu
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(6 pp.)
This paper has accomplished the modeling and simulation of a typical hydraulic brake valve, and analyzed its mechanical characteristics as well as control and output characteristics. In Simulink environment of Matlab software, the model of hydraulic brake valve was built and dynamic performance of the product was calculated. The performance parameter variation process was obtained during different operating modes and the affect of load on performance was also taken into consideration. By researching and analyzing on the simulation results under various operating conditions, an insight into the relationship and mechanism of product characteristics and performance indexes was gained. This is the first time to put forward a method of finding such a detailed model of the hydraulic brake valve. The research can be used to aid the design and analysis of dynamic performance according to the structure and working conditions of brake valve, as well as other hydraulic pressure servo valve. - Author(s): Wang Kuan and Huang Xiping
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(4 pp.)
Large aircraft's landing gear system is a complicated system which consists of various disciplines, including mechanics, hydraulics and controlling. Traditional simulation method which only considered single discipline of mechanics or hydraulics can't reflect the real performance precisely. To deal with this problem, both the dynamics and the hydraulic model of one large aircraft main landing gear system are developed respectively. Then these two models are integrated together through co-simulation interface to get the complete model for landing gear extraction system. Based on that, key parameters calibration method is then proposed. Finally, through comparing, the result of the simulation is well coincide with the test data, which proved the validity of the model. The model developed in this paper can be used for the analysis of landing gear extraction performance, and it could also be used as a reference to the optimization of landing gear system. - Author(s): Ji Teng and A.Z. Shahneh
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(8 pp.)
The MR (Magnetorheological) fluid is a kind of smart fluid and it can change its rheological property with external magnetic field. As the reaction is fast and controllable, it inspires the ideal of using MR fluid for shock absorber instead of conventional oil. In this paper, the property of MR fluid is introduced, the structure part of MR fluid landing gear shock absorber is designed including the magnetic generation and the damping performance under various magentic strength is analyzed. - Author(s): Liu Leilei ; Wang hongxin ; Xia Yubing ; Yang Zhenshan ; Ye Chenyi ; You Fan
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(4 pp.)
This paper developed a landing gear test interface unit for one type of aircraft. The test interface unit can set up the test interface, build up the test environment, get the test data, analysis and record the test data. The developed test interface is convenient to move and easy to build up the test environment for the landing gear system. This test interface unit is already successfully used for landing gear ground test for one type aircraft. It can also be used for landing gear system's manufacturing test, airline maintenance support or assistance to other systems' ground test. - Author(s): Sun Jing ; Qiang Gang ; Liu Jinsong ; Ma Xiaojun ; Niu Zujun ; Huang Xing ; Zhang Juan
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(4 pp.)
Hydraulic Fuse, as the safety protection device in brake control system, is used to prevent massive fluid leakage caused by pipeline breaking. The parameters, input flow, diameters of throttling orifice and inlet channel, dimensions of Moving Valve are the key factors that can influence its quantitative volume and closing time. In view of this, AMESim, mechanical hydraulic simulation software, is used to simulate and analyze the performance of Hydraulic Fuse. The results show that the quantitative volume and the closing time of Hydraulic Fuse will vary with diameters of throttling orifice and inlet channel, dimensions of Moving Valve. - Author(s): Kang Chongxuan ; Wang Bo ; Zhu Shixing
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(6 pp.)
Aircraft shimmy damper can effectively reduce the vibration of the aircraft nose wheel, and improve the comfort of travelling by plane and the pilot's safety as well. In fact, the magnetorheological shimmy damper has not been applied in the plane, but it has attracted widespread attention as a kind of smart control shimmy damper. By controlling the magnetic induction coil current of magnetorheological shimmy damper, the strength of the magnetic field can be changed, and passive control and semi-active control of the damping force of the shimmy damper can be achieved. In order to make the real-time control more intelligent and more efficient, based on the S-type hysteresis model in neural networks, this thesis puts forward a dual closed-loop control system with current closed-loop and damper piston rod displacement closed-loop, and we design and make a small control electrical system based on stm32 controller according to the strong non-linearity of the damping force output of the magnetorheological shimmy damper. The deep neural network algorithm is used to design multi-layer training learning model with multi-input and single-output. Combined with the experimental data of the shimmy test, the magnetorheological shimmy damper can effectively reduce the vibration of the landing gear under different conditions and reduce shimmy effectively. - Author(s): Wang Shihao ; Yan Zilin ; Meng Qingtang ; Xiao Yang ; Yang Hong ; Bai Lu
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(5 pp.)
During the course of accident investigation after many serious airplane accidents or incidents, the problem of calculating landing distance is raised to prevent aircraft overrunning the runway. The factors that affecting the landing distance and possible means to improve the landing performance should be fully acknowledged by air-framer. The definitions of actual landing distance and required landing distance is elaborated in this paper based on related airworthiness regulations and air-framer's experience. What's more, the effect of final approach speed, braking system, runway condition, runway friction coefficient and airport elevation for aircraft stopping performance is also explained by some flight tests and simulation. - Author(s): He Xuegong ; Liu jinsong ; Kang xiaoni ; Zhi qiang
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(6 pp.)
Aiming at the existing problems of two kinds of pressure servo valves, that is, nozzle baffle and jet pipe, commonly used in aircraft brake system at present, a new type of partial deflector jet pressure servo valve is proposed in this paper. After analyzed and researched the working principle of this partial deflector jet pressure servo valve, key components like torque motor, partial deflector jet amplifier and power-level slide valve, flow pressure gain coefficient for partial deflector jet is derived, mathematical model for torque motor is established and static and dynamic kinetic model is also established for partial deflector jet pressure servo valve. Therefore, a comparatively perfect theory system is formed for partial deflector jet pressure servo valve, which filled the gaps in partial deflector jet pressure servo valve of brake system in the research field in China, meanwhile, it offered guiding significance for the research and development of the same type of brake pressure servo valve, which laid a foundation for serializing the brake pressure servo valve. - Author(s): Guohui Chen ; Jinsong Liu ; Qianggang ; Xiaojun Ma ; Zhangjiao ; Kexun Luo
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(5 pp.)
Brake control system includes control law, hydraulic valves and sensors, normally the simulation model is not so accurate if only use Simulink model simulation result. This document integrating Simscape model and Simulink model, the physical model based on hydraulic valves and sensors structure could be created by Simscape, while behavior model based on requirements could be created by Simulink, this is an integration of physical and behavior model which is accurate enough for the development, validation and verification of brake control system. - Author(s): Jing Su ; Zhenshui Li ; Zehua Liu ; Erfeng Gao
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(4 pp.)
Hydraulic safety valves play an extremely important role in the hydraulic system design of aircraft. However, if the design and select of safety valves are not reasonable, it will cause much trouble to the hydraulic systems, and the most common and important one is the system vibration and whistles when the safety valves open, especially in the large high pressure hydraulic systems. Initial research pointed that these system vibration and whistles is related to the structure design of safety valves. In this paper, based on the indicated flow rate, open/close pressure and full open pressure, a new type of safety valve with small volume and weight has been designed, and then a physical simulation model based on the structure design has been established and simulated by AMESim and the structure of the valve has been optimized based on the simulation and analysis results of dynamic response of the valve. - Author(s): Zehua Liu ; Zhenshui Li ; Jing Su ; Cheng Qin
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(5 pp.)
The current situation of design of braking system is that high failure rate during landing and take-off status, and switching to emergency braking system automatically once faults appearing in normal braking system, it causes the braking system to fail to maximize its effectiveness. Based on this situation, a kind of reconstruction system of anti-skid braking system has been constructed by establishing the optimization model of shortest path based on the Dijkstra algorithm. In this paper, through establishing optimization model of signal flow, and reconstructing and optimizing the system by shortest path algorithm, the safety level of the anti-skid braking system of aircraft can be improved. The simulation results show that for indicated random faults, the system can be quickly and accurately reconstructed under braking process, and the safety of braking system can be improved. - Author(s): Luo Lin and Ding Xuebin
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(4 pp.)
Based on the control/monitoring architecture, a nose wheel steering system is designed, This paper introduces the steering system in the aspects of composition and operating principle, critical techniques and system validation results. Using results indicate that the system has complete functions, steering process is smooth, power steering angle can meet the requirements of runway width. The system has high reliability and good maintainability. Suggestions are given for consideration in system design. - Author(s): Jianghe Jia ; Zongxia Jiao ; Dong Sun ; Yaoxing Shang
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(6 pp.)
The key of aircraft anti-skid braking control is controlling the braking torque to keep the system operating near the optimal slip ratio and obtaining the maximum coupling coefficient. A braking active disturbance rejection control algorithm based on optimal slip ratio is being introduced in this paper. After establishing a nonlinear model of aircraft braking, an extended state observer is designed for its model, which provides the amount of disturbance in the braking process. These changes are used as the feedback of the active disturbance rejection control to adjust the output. This adjustment method can simplify the previous complex nonlinear links into the simple series of integral series. At the same time, the addition of the transition process makes the system will not produce drastic overshoot when dealing with larger steps, and it has a good effect on the adaptability of the system. The simulation results show that the control law improves the anti-skid performance of the aircraft and has good regulation performance for disturbances within a certain range. - Author(s): Liu Leilei ; Xia Yubing ; Li Chuang ; Yang Zhenshan
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(4 pp.)
This paper do a research on the pressure peak of landing gear uplock unlocking for civil aircraft. This paper first do a theory analysis and find out relevant factors like valve opening time, tube length, tube diameter and a restrictor. Then based on the AMEsim platform, a simulation model is built. From the simulation results, it can be known that the valve opening time, tube length, tube diameter and a restrictor all can have an obvious effect on the uplock pressure peak. An optimize solution is found after a trade-off analysis. - Author(s): Hao Zhang ; Yaoxing Shang ; Zongxia Jiao ; Shuai Wu ; Xiaochao Liu
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(5 pp.)
Aircraft braking system is essential to the safety of aircrafts and passengers. Traditional aircraft brake systems have some problems: dependence on the hydraulic energy from EDP; low reliability of complex hydraulic lines all over the landing gear, extra take-off weight brought by hydraulic lines, which could lead to aircraft accidents in severe cases. In this paper, an integrated pressure servo device based on double switching valves is proposed, whose operating mode is similar to that of ERA on the surface of civil aircrafts. Compared with the traditional aircraft brake system, extra hydraulic pipelines are canceled, and only electric is needed, which has great advantages in safety, reliability and economy. In this paper, the design and simulation of the braking system were introduced, the prototype was designed, which indicated the future development of this device is prospected. - Author(s): Haibin Yang and Leilei Chen
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(5 pp.)
The piston seal elements of hydraulic actuating cylinder are easy to be abrasion and vulnerable on the occasion of abominable conditions, especially in the area of aeronautical application. This paper is focus on a safety accident causes by fault of nose landing gear actuating cylinder, analyzing the possible effects on actuating cylinder's function and performance after secondary seal ring failure and giving the corresponding conclusions that this failure won't lead the down-lock failure, but it is a hidden trouble in cylinder and its structure design must be improved.
Simulation and Analysis Research on Dynamic Performance of Hydraulic Brake Valve
Research on Simulation of Aircraft's Landing Gear Retraction System Considering Multi-Discipline Coupled Factor
Design of Landing Gear Shock Absorber Using Magnetorheological Fluid
Research and Development for Landing Gear Test Interface Unit for One Type Aircraft
Simulation Analysis on the Performance of Hydraulic Fuse for Aircraft Brake
Design and Experiment of Magnetorheological Shimmy Damper Controller Based on Deep Neural Network
Analysis of Required Landing Distance on Performance Improvement of Civil Aircraft
Technology Research on Deflector jet Brake Pressure Servo-Valve
Analysis & Simulation Modeling for Brake Control System of Civil Aircraft
The Optimization Design of Safety Valve used in Aircraft based on AMESim Simulation
Research of Reconstruction Technology in Aircraft Anti-skid Braking System Based on Shortest Path Method
Design and Verification of Aircraft Electro-hydraulic Servo Nose Wheel Steering System
Aircraft Anti-skid Braking Active Disturbance Rejection Control Based on Optimal Slip Ratio
Research on the Pressure Peak of Landing Gear Uplock Opening for Civil Aircraft
A pressure servo device based on switching valves designed for more-electric aircraft brake system
Seal Failure Mode and Effects Analysis for Retractable Actuator of Landing Gear
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- Author(s): Wang Yangyang ; Liu Wenyi ; Pan Jun ; Wang Lu
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(6 pp.)
Airborne flame arrestor, which can effectively prevent flame propagation and spread so as to earn more evacuating time for passengers and crew, has been widely applied in aircraft ventilation system. In this paper, five main forms of flame arrestor element are discussed and their advantages and disadvantages are analyzed. Flow performance of these elements is calculated. The results show that the flow performance of crimped ribbon, metallic honeycombs and Cellular ceramics types are better than that of parallel plate and perforated sheet. - Author(s): Shao Yizhou and Wangyangyang
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(5 pp.)
The fuel tank explosion is a serious threat to aviation safety. Therefore, the federal aviation administration put forward the concept of Fleet Average Flammability Exposure (FAFE) and quantitative evaluation method after long-term research. The concept and method have been written into airworthiness terms. At present, China civil aviation administration has issued similar regulations in reference to the international standard. Never the less, there are few basic research efforts in the related field. In this paper, the fuel tank flammability exposure evaluation revised method based on domestic fuel is established from existing methods and principles combined with the difference between RP-3 and Jet A. Then the revised method is compared with original method, and the advantage of revised method is shown. At the same time, the relationship between flammability and equilibrium temperature is analyzed, and the optimization method is put forward. - Author(s): Xu Sanshu ; Zhang Xiaobo ; Yi Xiaohong
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(5 pp.)
Center of gravity (CG) design is a substantial part of aircraft design while fuel consumption is an important factor that changes the CG of an aircraft. Maintaining system CG within reasonable scope through systematic layout and fuel supply and transfer procedures is a key objective of fuel system design. As less artificial intervention is applicable to unmanned aerial vehicle (UAV), automatic matching and control of CG seem to be particularly important. Based on the design of a UAV fuel system, this thesis sets forth principles of CG control of the UAV and verifies the validity of such control. The study in this thesis may be used as reference in the design of UAV fuel system. - Author(s): Shiqiu Li ; Xiaobo Zhang ; Zhicong Wei
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(5 pp.)
With the continuous advancement of industry technology, fuel pumps are increasingly subject to vibration and noise problems in addition to high speed, high pressurization value, etc. In this paper, the noise of a fuel pump was tested and a design optimization to suppress the noise was proposed. The sound pressure level(SPL) was found exceeding requirements firstly. The numerical analysis model of the pump showed that the main reason of the noise is caused by pressure pulsation between the impeller and the vane. An optimized design of impeller and vane of the pump was proposed. The numerical results show that the pressure pulsation at the blade passing frequency(BPF) is significantly reduced. Finally, the optimized impeller and guide vane were machined and tested. Test result shows that the SPL of the fuel pump drops significantly, meeting the noise requirements. The research findings can serve as a reference for the design optimization of other aviation fuel pumps. - Author(s): Mou Pengtao ; Ji Yuan ; Li Guoqiang
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(4 pp.)
The fuel valve distribution motor mechanism is used to adjust the opening of the fuel valve in real time, and then precisely control the fuel flow of the pipeline, so as to achieve accurate flow distribution under different flight requirements of the aircraft. The output shaft of the motor-driven mechanism can be used to reach any given position from 0 to 90 degrees and locked. The potentiometer can feedback the current angle signal to reflect the flow of the pipeline. In this paper, we design a drive system of a brush DC machine based on DSP controller and introduce the scheme design, system design and circuit principle. Simultaneously we have developed the upper computer interface to be used to send control commands and display the current location information of the feedback when debugging in standalone machine. These programs are simple and quick to be operated. This electric mechanism has the advantages of high control accuracy, light weight, small size, high degree of integration, safety and reliability. - Author(s): Wentao He ; Shaoping Wang ; Chao Zhang ; Jie Wang
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(6 pp.)
The present article aims to analyze and evaluate how simple harmonic vibration influences the behavior of mechanical face seals of aero-engine pump. The purpose of this study is to provide a practical design method for engineering development. A dynamic model is developed to examine how dynamic parameters such as stiffness, damping and the frequency of simple harmonic vibration affect the leakage of mechanical face seals. Through the finite difference method and NewMark-β method show the validity of the dynamic model. - Author(s): Zhikang Li ; Zongxia Jiao ; Mei Yuan
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(6 pp.)
A numerical analysis method is presented for electromagnetic coupling problem in cables of aircraft fuel measurement system (AFMS). The reflection superimposition model of electromagnetic source is derived, then combined with transmission line (TL) equations and finite-difference-timedomain (FDTD) method, the hybrid FDTD method is improved. First, the electromagnetic environment of AFMS is analyzed, considering the actual geometric dimension of wing and characteristic electromagnetic source in AFMS. Then the coaxial cable is divided into external coupling system and internal coupling system, transmission line equations are used to model the above two systems, and the excitation fields are equivalent to distribution sources. Finally, the transient response on cable is obtained by TL equations with FDTD method. The numerical analysis result of reflection superimposition model is discussed in the given example. The influences of different reflection times are considered and it shows that the reflection superimposition model is stable and corresponded to actual response of practical problems.
Research on the Flow Performance of Airborne Flame Arrestor
Research on the fuel tank flammability exposure assessment method based on domestic fuel
Study on the Center Gravity Control Strategy of Tandem Aircraft Fuel Tank
The study and Optimization of noise in a fuel pump
Design of a Type of the Fuel Valve Distribution Motor Mechanism
Effect of Simple Harmonic Vibration on the Mechanical Face Seals of Aero-engine Pump
Electromagnetic Coupling Analysis on Coaxial Cable of Aircraft Fuel Measurement System
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- Author(s): Zhaojing Zhang ; Jianfeng Li ; Xibin Guo ; Jing Chen ; Pengfei Li
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(6 pp.)
According to the main joint movement of the hand, this paper proposes a single finger mechanism model containing two man-machine closed chain for a hand exoskeleton, which is based on the kinematics model of the hand. In order to increase the man-machine compatibility, one of the human-machine closed chain is the planar five bar mechanism including two human joints and three mechanical revolute joints, which has one degree-offreedom(DOF), the flexion and extension of each human joint can be realized. Another man-machine closed chain is the spatial six bar mechanism including one human joint, four mechanical revolute joints, and one cylindrical pair, which has two DOF, the flexion/extension and the abduction/adduction movements of human joint can be realized. Two man-machine closed kinematic model are analyzed, and got the finger joint motion position solution. The above study will provide a theoretical basis for further motion planning and control. - Author(s): An Yujiao and Jiang Huijun
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(6 pp.)
As a new alternative and tool, UAV system is widely used in military and civil fields. The UAV Ground Stationthe command center of the system with good ergonomics can reduce the workload of the ground station operator and ensure the mission to be accomplished efficiently and safely. The fuzzy synthetic evaluation method, which solves the problem of accurate and comprehensive evaluation to the UAV Ground Station, is applied in quantitative evaluation to the ergonomics of a general UAV ground station with more ergonomics factors and higher complexity. The research method is suitable for the evaluation of the ergonomics of other UAV ground stations. - Author(s): Lijing Wang ; Yanlong Wang ; Yinchun Chen
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(6 pp.)
Introducing touch-screen into civil airplane cockpit is inevitable trend for future cockpit design, which will certainly bring a disruptive revolution to the display and control pattern of airplane. Since the strict demand of safety in the civil aviation transport industry, sufficient evaluations and demonstrations are to be conducted before employing haptic technology on flight deck. Therefore, a survey on the opinion of aircraft designers and pilots on introducing touch-screen into cockpit was conducted through structural interview and focus group. 14 airplane designers and 6 airline pilots took part in the survey. The result of the survey is presented in this paper, including conclusion of the fundamental characteristics and advantages of haptic control, identification of potential display and control devices that can be replaced by touch screen, discussion of the challenges that the touch screen brought to the cockpit from human centric perspectives, and also some measures to ensure that touch screen technology can provide a more efficient and safer environment to the pilots. - Author(s): Huibin Jin ; Guihua Yu ; Guolei Zhu ; Bin Chen
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(5 pp.)
In order to analyze the difference of pilot`s eye behavior between emergency and normal situation, the eye movement test was performed on the Diamond 42 flight simulator. This test recorded the eye movement data during the simulated flight experiment, and analyzed the pilot`s eye movement changes in the three mechanical failures (Engine Failure, Attitude and Heading Reference Failure, Pitot tube Blocked) .Compared with the normal situation, the study shows in the situation of Single Engine Failure, the average saccade length has no significant change, but the overall saccade speed is significantly increased; however, the average saccade length and the overall saccade speed are significantly increased in the Attitude and Heading Reference Failure; lastly, there is no significant change of the average saccade length and overall saccade speed when the pitot tube is blocked. - Author(s): Zhang chen ; Bu xueqin ; Lin guiping ; Wang tao
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(7 pp.)
The Tanabe's 65-node model, based on the Stolwijk model, is an excellent one in the history of modeling the human thermoregulation system. This model divides human body into 65 nodes, some physical parameters and thermal properties are provided in details, and describes the typical physiological regulation with deviation signal. Based on 65-node model, the governing equations of skin blood flow, shivering and sweating are revised. After a human thermal response experiment, the initial temperature of nodes, distribution coefficients of external work and convective heat transfer coefficient of skin are corrected respectively to establish an individualized human thermoregulation model. The skin temperature deviation is controlled within 0.5 degrees. Finally, the revised model is used for another two possible experimental conditions, the prediction results are provided. - Author(s): Lijing Wang ; Jing Wu ; Wanqing Li ; Qiuyue Li ; Yongxue Liu ; Hui Wang ; Long Ma ; Yongzhi Yang
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(6 pp.)
The level of pilots' situation awareness directly affects the pilots' judgments and decisions. The improvement of the pilots' situation awareness level was an important task for pilots' training. In order to improve the pilots' situation awareness in flight navigation, this paper studied the main factors that influence the situation awareness of pilots in flight navigation training, and provided theoretical basis for the targeted training. Using the Delphi method, we selected and established the main Influencing factors of the pilots' situation awareness in every phases of flight navigation training, and also established hierarchical structure system. We got the judgment matrix assigned by four mature pilots and three aerospace theoretical researchers jointly and establish judgment matrix with comparison coefficient for the hierarchical structure of the factors affecting the pilots' situation awareness in flight navigation. We check the consistency of judgment matrix. According to the weight coefficient of each factor, we sorted and analyzed the main influencing factors. In contrast with airline flight standard of the “Airline Transport Pilot License and Aircraft Type Practice Test StandardüAircraft”, we checked the main factors affecting the pilot's situation awareness with a large weight coefficient that were basically consistent with the main requirements in navigation training. These factors are aircraft attitude control, track correction, landmark recognition; task planning during flight preparation phase, autonomous preparation; landmark identification during the departure phase, and flight to the tower during the return flight phase.
Configuration Design and Kinematic Analysis of the Self-Alignment Type Finger Exoskeleton Mechanism
Study on the application of fuzzy synthetic evaluation method in the ergonomics evaluation of UAV Ground Station
Survey on introducing touch-screen into civil aircraft cockpit: opinions of aircraft designers and pilots
Analysis of Pilot Eye Behavior in Emergency of Mechanical Failure
An individualized human thermoregulation model based on Tanabe's 65MN
The Research on Influence Factors of Pilots' Situation Awareness Upon Analytic Hierarchy
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- Author(s): Xiaoming Yuan ; Shiyi Zhao ; Chu Wang ; Lijie Zhang
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(6 pp.)
To improve the jet performance of a fire water monitor, the monitor head with three different inner contour lines were designed. Based on FLUENT, the calculation domain was defined geometrically and then the cloud pictures of the flow velocity, pressure, turbulence kinetic energy and multiphase flow of the fluid field in the nozzle and jet were obtained, based on which the optimal structure of each model can be selected. The simulation result can provide the theoretical reference for the design of a monitor head. - Author(s): Yong Li ; Xuemei Zong ; Xiaoming Yuan ; Shiyi Zhao
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(6 pp.)
In order to evaluate the hydraulic performance of a regulator, the pressure loss and the stabilization performance of the regulator installed in the fire water monitor were introduced. The effects of structures on a regulator were investigated by the structural model made in UG and the flow simulation conducted in ANSYS. The hydraulic performance of a star-shaped regulator was analyzed with different structure parameters, such as the blade number, axial length and rounded-corner. The effects of structure parameters on the regulator were revealed, based on which the hydraulic performance of the improved regulator with different blade numbers was analyzed. The results show that the improved regulator with two cross-sections in dislocation and six even-distributed blades has the better hydraulic performance. The preliminary experimental results show that the improved regulator can improve the jet range of a fire water monitor. - Author(s): Yu Chunyu
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(4 pp.)
In airborne applications false alarms can be very costly, as they may force a pilot to an emergency landing at the next airport. Dust is the major source of false alarms in cargo compartment applications. The dust suspending in air is the main reason of trigging false alarm of smoke detectors. Long time deposition of dust in the chamber of a smoke detector may cause the drift of the threshold and cause false alarm or missing alarm. Also the increase of dust concentration in air in a short time may also cause false alarm of smoke detector. The ability of anti-dust pollution of a smoke detector is a key factor for the reliability of a smoke detector. A dust test equipment for quantitative research of dust pollution has been designed and built up at Shenyang Fire Research Institute. The main body of the equipment consists of dust test chamber, dust concentration meter, optical smoke density meter, dust generator and computer. Two patterns of tests have been carrying out for transient disturbance and long-term deposit effect respectively. From the result criteria, we can tell the differences between different smoke detectors in their resistance to dust interference. - Author(s): Junchao Zhao ; Song Lu ; Dan Zhang ; Hui Yang ; M.U. Shahid
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(6 pp.)
Aircraft fire is one of the causes of aircraft failure and significant research work is undergoing for its prevention. This research paper deals with the investigation of a pattern for aircraft fire accidents. For this purpose, the correspondence analysis (CA) is used. Initially, the probability of aircraft fire accidents in different flight phases is calculated. Three factors (i.e. the phase of aircraft flight, extent of fire and month of flight) are used to explore the inner relationships with damage degree through correspondence analysis. Through CA mapping, it is found that fire accident causes high degree of damage when phase changes. FSCE (Fire & smoke-inside the cabin & external) and F (Fire-extent unknown) easily lead to serious aircraft damage. It is also observed that fire can cause huge damage to aircraft round the year, except the months of May and September. - Author(s): Yu Guan ; Song Lu ; Han Jieqian ; Wei Yuan ; Heping Zhang
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(5 pp.)
The research of gas concentration distribution is critical for verifying the validity of aircraft fire suppression system which has the characters of quick release and rapid dispersion, and for this the response of the concentration detection equipment should be fast. This paper analyzes the response/recovery properties of the gas sensing technique based on the detection of pressure difference. It is an aspiring detection method and widely used for the evaluation of aircraft fire suppression system. The gas CBrF3 was used in the experiments. Three influence factors including gas concentration, geometry structure of the sensing part, and the size of sample tube are studied. By studying the effect of concentration, it was found that the recovery time was higher than the response time, and with the increase of the CBrF3, the recovery time increased. By studying the influence of geometry size of the detector, it showed the response/recovery time could be improved by increasing nozzle throat diameter, and the longer the length or the bigger the diameter of the tube were, the slower the response of device was. These finding can be instructive for both sensor design and practical concentration detection. - Author(s): Hanjie Qian ; Yu Guan ; Yuan Wei ; Song Lu
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(7 pp.)
Gas concentration detection device is widely used in various fields. This paper is focus on a pressure differential gas concentration measuring device [1] used in aircraft fire extinguishing system. One of the advantage of the device is the tiny structure in the device but it also leads to the hinder to measure the behavior of the flow in this region by experiment. Here, with the help of numerical simulation, we study the flow behavior in the equipment and we also do some research on the effect of pipes structure on the measurement results. The pressure field, temperature field, velocity field and the flow behavior is presented using the finite volume based solver STAR-CCM+. The effects of different diameter and arrangement of the pipes on the measurement results were compared. It is found that reducing the volume of the whole device will effectively improve the sensitivity and reduce the response time. The adjustment of the structure of the pipe can also reduce the response time. The present results help to understand the flow phenomena occurring in the device and optimizing the structure of the pipes in the equipment. - Author(s): Neng Tao ; Dan Zhang ; Wei Yuan ; Song Lu ; Yong Zhou ; M.U. Shahid
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(5 pp.)
With the continuous innovation in electronic circuit boards and the shortening of their life cycle, huge amount of solid waste is being generated. The rational disposal of WPCB and recycling is a matter of environmental concern. This paper investigates the thermal decomposition properties and the kinetic analysis of aviation WPCB (Waste Printed Circuit Board) substrate. The thermal decomposition process of the substrate in pure nitrogen and air atmosphere is investigated using thermogravimetric-differential thermal analyzer (SDT Q600) and the computational theory of the Coats-Redfern method. The thermogravimetric analysis (TGA) was used to investigate the pyrolysis characteristics and reaction kinetics of the aviation WPCB substrate. Differential thermal analysis (DSC) was used simultaneously to determine the reaction enthalpy under the air and the nitrogen atmosphere. The experimental results yield the thermal analysis of the aviation WPCB substrate and provide a scientific base for resource utilization and clean, efficient and safe disposal of the aviation WPCB. - Author(s): Zhang Ruihua and Jiang Hongyan
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(5 pp.)
Based on the perspective of a civil aircraft hydraulic energy system, this article provides a statement of compliance for the fire safety provisions of the CCAR25-R4 applicable hydraulic energy system for the system's fire safety. Analysis shows that the aircraft's hydraulic system complies with 863, 981(a), 1182(a), 1183(a), 1185, 1189(a)(c)(d)(e)(f)(g) (h ), 1435 (b) (4), the design of the hydraulic system can meet the requirements of fire protection provisions to ensure flight safety. - Author(s): Enhao Xing ; Jiaming Jin ; Zhaojun Zhang ; Renming Pan ; Qunwei Li ; Jiawei Zheng
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(6 pp.)
In this study, AMESim software was used to simulate the process of halon 1301 fire extinguishing agent discharged from expansion nozzle, and the influence of nozzle outlet cross-sectional area, nozzle length and different expansion types of nozzles on the flow rate at the nozzle outlet were analyzed. The result shows that the outlet flow rate of the sudden expansion nozzle is less affected by the length of the nozzle, and the maximum flow rate at the outlet decreases with the increase of the outlet cross-sectional area. From the gained data, in the range of 0°~45°, the maximum outlet flow rate of the progressive expansion nozzle decreases with the increase of the outlet crosssectional area and increases with the increase of the nozzle length. When the outlet cross-sectional area and nozzle length of the two nozzles are both the same, the maximum outlet flow rate of the progressive expansion nozzle is larger than that of the sudden nozzle, and the difference between them decreases as the expansion angle increases when the outlet cross-sectional area is constant.
Effects of Physical Parameters of Multiphase Flow on Fire Water Monitor Based on Fluent
Effects of Structural Parameters on Hydraulic Performance of Flow Regulator
Quantitative dust test technology for point-type smoke detectors
Correspondence Analysis of Aircraft Fire Accidents: Damage Degree and Three Influence Factors
Study on the response/recovery properties of the gas sensing technique based on the detection of pressure difference
Numerical simulation of the influence of the pipes structure on the measurement results of a pressure differential gas concentration measuring equipment
A Study of Thermal Decomposition Properties and Kinetic Analysis of Aviation WPCB Substrate
Analysis of Hydraulic System with Fire-Protection Airworthiness Items in a certain type of Civil Aircraft
Simulation on Flow Rate Characteristics of Gas Fire Extinguishing Agent with Expansion Nozzle Based on AMESim
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- Author(s): Shenglan Li ; Xianzhi Niu ; Xiping Huang
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(5 pp.)
With the vigorous development of computer technology, the CFD method has played an increasingly important role in aircraft design. In order to study the correlation between CFD and wind tunnel test more accurately,the steady flow of the supercritical airfoils NASA 0714 was numerical simulated. Based on the basis of previous research, the experimental data is corrected. So as to further improve the correlation between wind tunnel test data and CFD calculation results, a set of optimum CFD calculation conditions are found in the corresponding wind tunnel test conditions. Based on the steady data correction, the SA model is used to numerically simulate the buffeting test of NASA0714 airfoil with the same correction of angle of attack and Mach number, finding the buffeting boundary of a certain state. By comparing with the test data, it is concluded that the buffeting boundary under the CFD calculation conditions is ahead of the buffeting boundary obtained by the test. - Author(s): Deng Yipan ; Liu Yinshui ; Miao Na ; Wu Defa ; Li Xiaohui
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(6 pp.)
Oil-free designed miniature multi-stage swash plate compressor holds the advantages of compacted size, lightened weight and clean output gas. It can be typically applied in aircraft and ground systems for cooling, pneumatic catapult and scuba diving etc. High sealing efficiency of high pressure gas can guarantee the proper working of the compressor. Due to the peculiar demands to the pressure level, lubricating condition and overall weight and dimension, clearance seals can embody greater advantages when compared to the contact seals such as piston rings or packs. In our study, a mathematical model of flow in the clearance gap between the piston and the cylinder was established. The motion of pistons was considered due to their effects on the gas pressure and sealing length. Some sensitive parameters were analyzed to reveal their influence on the properties of clearance sealing. Therefore, the optimal range of these parameters were obtained to provide an overall excellent sealing performance in the miniature multi-stage swash plate compressor. - Author(s): Ying-ting Wang and Gang Bao
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(5 pp.)
The requirement for energy harvesting technology is steadily growing in the field of self-power wireless sensor system for pneumatic system. In this paper, a cantilevered polyvinylidene fluoride layer generator is presented which capture energy by dissipative in the pneumatic system. The purpose of this study is to research an energy generator excited by the fast moving air. A generator model is designed and it consists of a PVDF layer and a cylinder. the fast moving air becomes when the dissipative air come out of the air pipe. A flexible PVDF layer is fixed in different distances from the air pipe to the PVDF surface. The cantilevered bend theory of PVDF layer has been analyzed. The simulation of PVDF bending is calculated which takes a cylinder in one side. The energy from the dissipative air load can be harvested through the deformation of the PVDF. The test system is built and the experiments are designed to explore the relationships between the generated voltage and the compressed air parameters. With the cycle increases, the voltage is increased. With the mass increases, the voltage is decreased. The output voltage is 11.93 V across the mass of 1.0 g, flow of 250 Llmin and cycle of 2.0 s. - Author(s): Dong Zhu and Changhai Liu
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(4 pp.)
A two-dimension model of a pneumatic system consisting of a constant volume chamber, an orifice and a pipeline is established. The unsteady flow field and temperature profile are simulated with the finite volume method (FVM) for a number of charging-discharging cycles until a negligible temperature change is observed. The minimum temperature on outer surface is found on the orifice. The temperature increases during the first half cycle (charging period) and drops during the second half cycle (discharging period). After a number of cycles, temperatures in most locations within the system do not change with time significantly. This work is expected to help evaluate the operating performance of a pneumatic system involving condensation and evaporation. - Author(s): Qihui Yu ; Maolin Cai ; Dan Wu ; Jianguo Meng
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(5 pp.)
The following article published in IET Conference & Seminar Publications, CSAA/IET International Conference on Aircraft Utility Systems (AUS 2018), Yu, Qihui; Cai, Maolin; Wu, Dan; Meng, Jianguo: 'A study of reflection effect in air-coupled Lamb wave gas flow detection system' CSAA/IET International Conference on Aircraft Utility Systems (AUS 2018), DOI: 10.1049/cp.2018.0267 has been retracted due to a breach of the IET's Policy in Relation to Plagiarism, Infringement of Copyright and Infringement of Moral Rights and Submission to Multiple Publications, with regards to the following already published work, Fan, Z; Jiang, W; Cai, M; Wright, W.M.D: 'The effects of air gap reflections during air-coupled leaky Lamb wave inspection of thin plates' Ultrasonics, 2016, 65, pp. 282-295, DOI: 10.1016/j.ultras.2015.09.013 (https://doi.org/10.1016/j.ultras.2015.09.013). - Author(s): Yuhui Zong ; Jing Zhang ; Gang Bao
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(6 pp.)
The electric actuator has the advantages of simple structure, high positioning precision and strong anti-interference ability. But in the vertical condition, when the load is high, the electric actuator needs to consume great power to keep the load position unchanged. The output of the cylinder is larger, so it is more convenient and energy-saving to maintain the load position in the vertical working condition. However, due to the influence of nonlinear factors such as friction, the positioning accuracy of the pneumatic position servo system is not high. In order to solve the problem of low positioning accuracy of pneumatic servo system and the problem of power consumption of high-power electric actuator, a pneumatic-electric hybrid control system is proposed in this paper. The mathematical model proposed in this paper consists of two sub modules, which are the electric actuator position control module and the aerodynamic servo module. The research results show that the new control system can ensure the positioning accuracy in the case of large output. - Author(s): Tong Fei and Zhu Hongtao
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(6 pp.)
As the most widely used non-contact sealing structure in aero engines and gas turbines, labyrinth seal is often used to reduce the leakage of compressor and turbine regions. During the working process of engines, the rub-grooves are formed, due to the abrasion of the bushing, which leads to the increment in the leakage of the labyrinth seal. To improve the seal performance of a rub-grooved labyrinth seal, seals with bulges have been numerically investigated. Results show that both pressure ratio and bugles' size have strongly effect on the seal performance of rub-grooved labyrinth seals. Compared to non-bulge seal, bulges destroy the continuity of the jet boundary layer and change the direction of the jet flow, which decrease the leakage effectively. The discharge coefficient can be decreased 32%, when the pressure ratio is 2. The results show that the most important parameter that influences the discharge coefficient is the height of bulge. The seal efficiency can be raised 20%,when the bulge' s height is 0.1mm,and when the height is 0.3mm,the seal efficiency can be raised to 40%.Bulge's width has some effect on seal performance, but not obvious. Within the scope of this study, data also reveal that the relative position between the bulge and rub-groove has little influence on rub-grooved labyrinth seal. - Author(s): Xiaokai Chi ; Shaoping Wang ; Yixin Zhang ; Xingjian Wang ; Qing Guo
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(6 pp.)
This paper presents a tailless butterfly-type flapping wing aircraft, which is inspired from natural morpho insects. Based on the butterfly shape, the proposed butterfly-type flapping wing aircraft focuses on low aspect ratio. In order to reduce the weight, the aircraft carries out optimal design and determines the structure with thin membrane, ultra-high modulus carbon rods and custom connections. Through a large number of biological observation to mimic body movement and wing trajectory, this paper proposes a new kinematic model and analyzes its performance of prototype with computational fluid dynamics software. Flight test indicates that the proposed tailless butterfly-type flapping wing aircraft can realize one minutes cruising in specific condition. - Author(s): Wang Jia ; Xu Weiging ; Sun Wenjun ; Cai Maolin
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(5 pp.)
In this paper, a solar-powered cogeneration system is designed. This system can meet the needs of a small family for cooling, heating, power, and hot water, and according to the surrounding environmental conditions, the system can transform into different modes. Subsequently, the experimental platform was set up and the performance test of cooling and hot water mode function of the system was completed. With an experimental lasting time of 45 minutes and the compression frequency of 40Hz, pressure and temperature values needed at different ports were measured and collected. The result shows that, during the cooling process, the maximum power was 1292.29W, and the maximum cooling COP was 2.03. While heating water for the family, the maximum power was 1350W, and the corresponding COP was up to 2.12. The results provide a basis for the design and application of solar thermal power combined cooling system.
Study On the Correlation Between the Dynamic Test of Airfoil Wind Tunnel and CFD Calculation
Analysis on Clearance Seals in Miniature Multistage Swash Plate Compressor Considering Piston Motion Effects
Modeling and Characterization of a Cantilevered Polyvinylidene Fluoride Layer Generator Impacted by Dissipative Pneumatic Pressure
Simulation of Temperature Field within an Unsteady Pneumatic System with Constant Volume
A Study of reflection effect in air-coupled Lamb wave gas flow detection system
Research on pneumatic-electric hybrid control system based on velocity positive feedback in vertical working condition
Effects of Bulges on the Seal Performance of Rubgrooved Labyrinth Seal
A Tailless Butterfly-type Ornithopter with Low Aspect Ratio Wings
Experimental study of a combined heat-power-cool system
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- Author(s): Xudong Shi ; Jianhui Sun ; Shaoshuai Yuan ; Fujun Ying ; Zhaorong Sun
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(6 pp.)
The ignition component plays an important role in the aero engine, any faults happen to the engine ignition component may significantly influence the ground or air starting performance, and poses a great safety hazard to the normal operation of the aero engine. In order to ensure the reliability of the ignition component, specified test is necessary to be performed during both infield and outfield overhaul. However, large equipment is not suitable for outfield testing and seriously affects test efficiency. To solve this problem, the existing test methods for infield/outfield overhaul and test principle for spark parameters are analyzed at the beginning. Further, a portable outfield test system for aero engine ignition component is designed, which is capable of monitoring spark parameters during the outfield overhaul, by accurately measuring the ignition voltage and current waveform. - Author(s): Yuanyuan Yu
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Aiming at providing a safe dynamic environment for the test objects of large mass, long cantilever and high above ground in flight tests, a kind of high speed rocket sled with the vibration reduction system was developed. The test adopts dual-track rocket sled equipped with wide frequency multiple dimensional vibration reduction system for the first time. The structure of vibration reduction system and the associated parameters were investigated and determined using techniques of parameter identification, dynamics simulation analysis and shaking table tests. The design meets the requirements of the vibration environment and bearing capacity of full-size and high-overload supersonic tests. The test results show that the vibration environment provided by the vibration reduction system is within the allowable range of test objects, and the values of acceleration amplitude are close to the flight test. - Author(s): Yunfei Tao ; Yuping Huang ; Jing Chen ; Pengfei Li ; Miao Wu
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(7 pp.)
This paper presents a single-station, multipoint and time-shared position and attitude measurement method of roadheader based on iGPS, which can accurately and unmannedly measure the angle of deviation and offset distance of roadheader. The position coordinates of the receivers fixed at different locations on roadheader body are measured by the single-station, multipoint and time-shared position and attitude measurement system based on iGPS, and the angle of deviation and offset distance of roadheader are calculated through the receiver position coordinates. The mathematical model between the angle of deviation and offset distance of roadheader and the position coordinates of the receivers and measurement parameters is established, and the error transfer equation of angle of deviation and offset distance of roadheader are deduced by the mathematical model and random error modeling theory. The regularity of measurement error of angle of deviation and offset distance of roadheader is studied in different the spacing between the laser stations and the measuring distance between the laser station and the roadheader according to the error transfer equation of angle of deviation and offset distance of roadheader. In order to proof the accuracy and reliability of the method to study the regularity of measurement error of angle of deviation and offset distance of roadheader, a set of high-precision total station experimental system is designed. The experimental results show that the regularity of measurement error of angle of deviation and offset distance of roadheader are basically the same in theoretical simulation and experimental study respectively. To meet the requirements of the use of coal mine roadway, although slightly biased in value. This technology can be applied to the assembly process of large aerospace equipment, and has great application value and theoretical value.. - Author(s): Guoxiong Luo ; Jun Liu ; Wenbo Shen ; Hongyi Gao
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(4 pp.)
In rocket sled tests, a new automatic tracking technique based on image recognition is proposed to adapt to the development of intelligent technology. The automatic tracking system is mainly composed of tracking camera, shooting camera and tracking turntable. This tracking technique adopted Camshift as the main algorithm, and at the same time designed and optimized the tracing algorithm of the key points such as the target capture of the rocket sled, the ejection seat coming out of the cabin, and man-seat separation, there by achieving the automatic tracking of the whole process of rocket sled ejection seat test. In addition, by conducting a simulation experiment with the angular velocity of 120°/s and the speed of 1.2 Ma, the feasibility of automatic tracking system servo control strategy is verified. Based on this automatic tracking technology, the design of automatic tracking test system for seat ejection test is being carried out. - Author(s): Han Chao and Wang Yin
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(4 pp.)
Because of the advantages such as simple structure and less layers of winding, the step-winding mode has been widely used in Linear Variable Differential Transformer (LVDT). In order to realize the output in full stroke of LVDT, the length of core must be longer than twice the length of LVDT's full stroke. Due to the divergence of magnetic field lines, the strength of magnetic fields is decreased shapely at the end of frame, so the number of secondary coils at the end of the frame should be increased to improve the linearity. At the same time, this method will cause the fluctuation of sum voltage, which is bad for fault detection. The sectional winding mode is proposed here to improve the linearity of output voltage and the stability of sum voltage. In this paper, the design idea and process of sectional winding mode are presented in details. The improvement in linearity of output voltage and the stability of sum voltage was proved by the simulation and experimental results. - Author(s): Chenying Liu ; Xuesong Luo ; Shaoping Wang
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(6 pp.)
Accurate measurement of three-axial force is essential for dexterous manipulation of grippers. Capacitive sensor is one of the most effective ways to achieve tactile sensing. However, current researches mainly focus on measurement of normal forces. In order to improve the accuracy of measuring tangential force and further reduce the size of sensors, a highly-decoupling triangular capacitive sensor structure, which is based on floating comb electrodes, is proposed in this paper. An analytical model that combines normal force and tangential force together is established and corresponding formulas are put forward. The model is validated by Finite Element Analysis (FEA). The experimental results show that the proposed structure achieves high decoupling of tangential forces with a smaller size compared with previous structures. - Author(s): Wang Kaisiyuan and Cao Jiwei
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(6 pp.)
High-speed motors have been widely used in numbers of industrial areas, such as spindle system, compressors, flywheel energy storage and distributed generation etc. Therefore, mature testing approaches aimed at evaluating the performance of motors and the manufacturing process are in urgent need at present. In this paper, we introduce a multifunctional high-speed motor testing system, which is used in an electromagnetic torque loading testing platform, illustrated in detail as well. For the sake of precise evaluation, a modified method of active power calculation and a new method based on variable sampling frequency and variable window length are proposed in this paper. The results in simulations and the experiments give support to the effectiveness of these methods and the comparation of analysis results between these methods and a YOKOGAWA power analyzer product has also been shown in this paper. - Author(s): Yang Ouyang and Zhang Yuan
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(5 pp.)
By non-contacting measurement, the inductive proximity sensor overcomes disadvantages such as short service life and unreliability of position detection components like micro-switch. And high environmental resistance of magneto-resistive proximity sensor is realized by using wholly-metallic sealing housing. Because the coil loop resistance is easily affected by ambient temperature while the coil inductance of inductive proximity sensor is generally not affected by it, an algorithm to calculate the coil inductance is proposed. For ease of engineering, the design of inductive proximity sensor unaffected by ambient temperature is realized by approximate calculation and error estimation. The actual test shows that this solution has better temperature adaptability and engineering conditions than the traditional one. - Author(s): Wang Jian and Xue Long-Xian
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(5 pp.)
The aircraft engine bleed air simulation test bench temperature control system simulation parameters include the bleed air pressure and temperature. The temperature simulation key unit--electric heater has the characteristics which are wide temperature range, nonlinear and large inertia. If only a single temperature parameter is used as the feedback point in the control system, it can't accurately describe the bleed air simulation test bench temperature control system's characteristics, greatly influence the control accuracy. The conventional control strategy can't solve the contradictions of the response speed and stability of system. According to the above problem, this paper proposes a method based on humanoid intelligent control, after theoretical modeling of the air flow, heating power and outlet temperature of the heater as the control characteristic parameters, the total analysis was conducted. Heating control process is divided into three phases: Full power output, balance feedback, steady state adjustment. On the engine bleed air simulation test bench test results shows, temperature control system based on humanoid intelligence have advantages as follows: control high precision, low Overshoot amount, both system response speed and stability have the very big promotion. - Author(s): MaoLin Cai ; XiaoShuang Wang ; Zichuan Fan ; Jian Chang
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(6 pp.)
The following article published in IET Conference & Seminar Publications, CSAA/IET International Conference on Aircraft Utility Systems (AUS 2018), Cai, Maolin; Wang, Xiaoshuang; Fan, Zichuan; Chang, Jian: 'Research on the wave field characteristics of leakage Lamb wave based on air coupling technology' CSAA/IET International Conference on Aircraft Utility Systems (AUS 2018), DOI: 10.1049/cp.2018.0281 has been retracted due to a breach of the IET's Policy in Relation to Plagiarism, Infringement of Copyright and Infringement of Moral Rights and Submission to Multiple Publications, with regards to the following already published work, Fan, Z; Jiang, W; Cai, M; Wright, W.M.D: 'The effects of air gap reflections during air-coupled leaky Lamb wave inspection of thin plates' Ultrasonics, 2016, 65, pp. 282-295, DOI: 10.1016/j.ultras.2015.09.013 (https://doi.org/10.1016/j.ultras.2015.09.013). Dr. Zichuan Fan was added to the author list of the retracted paper without his knowledge or consent; he was unaware of and not complicit in any unethical behaviour. - Author(s): Zhi-sheng Jin and Guo-xiong Luo
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(5 pp.)
In civil aircraft passenger seat dynamic impact test, the occupant head target for acquisition head path might be obscured by the body motion. Based on the airworthiness standard of passenger seat in civil aircraft SAE AS8049 and photometric data acquisition procedure for impact test SAE ARP5482, three kinds of auxiliary target plates were researched to gather the complete data of occupant head path. The auxiliary target plates were designed and evaluated. The better kind auxiliary target plate was selected and used in occupant head path test in civil aircraft passenger seat. - Author(s): Xiaojiao Zhao ; Lei Han ; Yanbo Wang ; Huimin Ren ; Yang Yang ; Ziliang Shangguan
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(5 pp.)
Efficient and rapid recognition of aircrafts is of great significance in the fields of air traffic control, airport monitoring and military surveillance. In this paper, a method of fusion moment invariant aircraft recognition (FMIAR) on multisource information is proposed, which can deal with the multisensor images in real-time and eliminate the influences of image translation, scaling, rotation and background noise. Furthermore, unreliable sensors can be cast off tactically to identify the aircraft type. Experiments show that FMIAR satisfies requirements of effective real-time online identification. - Author(s): Zhentian Liu ; Guangsen Wang ; Chengmei Lin ; Zhiwei Wang ; Jing Li
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(6 pp.)
The more electric aircraft (MEA), belonging to the large-scale complex electromechanical system (LSCES), always has a large-scale complex structure, of which the design, testing, and evaluation may be a challenging task. In order to analyze the impact of various factors on the system performance and reduce the potential risk, it is advantageous to establish a hardware-in-the-loop (NIL) real-time simulation platform for MEA. From this purpose, some key processes are suggested to clear the way for an efficient and accurate design. First, the principles of system partitioning and high-performance communication network are presented for distributed parallel computation. Then, algorithms are discussed and compared aiming to compensate intersimulation time-step switching error caused by high-frequency switches which are widely used in MEA. Finally, an automation test method based on Monte Carlo (MC) and Genetic Algorithm (GA) methodology is proposed. In the experimental part, a permanent magnet synchronous motor (PMSM) in NIL mode is presented to demonstrate the practicality, with the results of the offline and real-time simulation compared. In short, this paper provides a guidance for establishing an NIL platform for LSCES. - Author(s): Cao Jiwei and Lei Qun
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(5 pp.)
High speed motors have been widely used in many industrial areas, such as spindle system, compressors, flywheel energy storage and distributed generation etc. Now, motors are developed to higher speed and power. But the high speed motors test technology became a difficult problem because of rotor dynamics and machining tolerance. Therefore, this paper presented a novel test system to solve this problem that motors are loaded with high speed. Through the high speed motor test system, we can test the motor below the 40000rpm, 20kW. And the test system could supply the detailed running data for high speed motor design. - Author(s): Yingchun Chen ; Deng Ming ; Xinhua Wang ; Zia Ulah ; Qingfeng Pan ; Yizhen Zhao
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(6 pp.)
Harmonic eddy current magnetic field inspection, as one of pipeline nondestructive inspection technology, can be accurately and efficiently used to estimate the damage of buried steel pipeline. Based on the principle of harmonic eddy current magnetic field detection, a theory model of double frequencies alternating excitation was established, and a non-contact coil array detection probe was also designed. An indoor experimental platform was built to proceed experimental study on the differences in magnetic induction intensity distribution for various pipeline defect species, and the variation in magnetic induction intensity for different excitation frequencies and input voltages. Results showed that change in resistivity due to the pipeline defect causes a nonuniform current distribution that distorts the induced magnetic field, resulting significant increase in the magnetic induction intensity; While moving the probe along the surface of the pipeline, better detection results can be achieved for various defect species with greater defect depth and smaller angular orientation between defect trend and moving direction; Similarly a robust change in the magnetic induction intensity can be observed with low signal frequency of harmonic power supply and greater input voltage of detection probe. The researches done prove that harmonic eddy current magnetic field inspection can effectively realize the nondestructive damage detection of buried steel pipeline. - Author(s): Zhenshui Li ; Chengyong Gao ; Xingjian Wang ; Shaoping Wang
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(5 pp.)
In this paper the key elements and methods of top-level design for iron bird are elaborated, including the main aspects of demand study, functional architecture, modular architecture and equipment architecture. Design cases are used for detailed demonstration.
Design of a Portable Outfield Test System for Aero Engine Ignition Component
Study on the Heavy-load Vibration Reduction Platform Based on the Dual-track Rocket Sled
Study on Measurement Error of Angle of Deviation and Offset Distance of Roadheader by Single-station, Multipoint and Time-shared Measurement System Based on iGPS
A New Automatic Tracking and Shooting Technique Used in Seat Ejection Test Based on Image Recognition
Research on the influence of winding mode in LVDT
A Highly-Decoupling Triangular Tactile Sensor Structure for Three-axial Force Measurement Based on Floating Comb Electrodes
A New Testing System For High-Speed Motors
Approximate Engineering Method for Detection of Magneto-resistive Proximity Sensor
Design of engine bleed air simulation test bench temperature control system based on humanoid intelligence
Research on the Wave Field Characteristics of Leakage Lamb Wave Based on Air Coupling Technology
Research on Auxiliary Target Plate in Civil Aircraft Passenger Seat Occupant Head Path Test
Fusion Moment Invariant Recognition of Aircraft
A Design of Hardware-in-the-loop Real-time Simulation for Large-scale Complex Electromechanical System
Design and Experiment of High Speed Motor Test System
Research on Harmonic Eddy Current Magnetic Field Detection of Buried Steel Pipeline
The Top-Level Design Architecture of Iron Bird
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- Author(s): Xiaofeng Li ; Shinan Chang ; Mengyao Leng ; Weidong Yu
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(6 pp.)
Numerical simulation was conducted for the air and water droplets two-phase flow along the icing wind tunnel. The mass and heat transfer models between droplets and cold air were built by using Lagrange method. The temperature, diameter, velocity and trajectories changes along the duct for water droplets with different initial diameter were calculated; the influences of the velocity and diameter changes on the impingement property were studied and four different three-dimensional distributions of local collection coefficient along the wingspan were calculated under 4 different kinds of nozzles arrangements. The results showed that the water droplet temperature has a good following of the airflow; evaporation effect on smaller droplets is heavier than that on larger droplets; the trajectory of small droplet almost coincides with the air streamline, while large droplet deviates greatly from air streamline; the distribution of small water droplets in the test section can be controlled by activating different height nozzles, while large droplets are concentrated at the center of the test section; the change of the velocity will lead to an increase in the local collection coefficient, while the change of diameter will lead to a slight decrease in the collection coefficient; the distance between adjacent nozzles has a decisive influence on the uniformity of the icing cloud in the test section, and the smaller the distance is, the more uniform the icing cloud distribution is. The uniformity of icing cloud can only be improved slightly when the distribution of nozzles are changed from aligned arrangement to staggered arrangement in the certain numbers of nozzles. - Author(s): Hao Dong ; Longfei Li ; Jiangfeng Wang ; Cong Xu
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(5 pp.)
First of all, a numerical method is developed for automatic icing simulation on aircraft which consists grid generation, ice generation, grid upgrade after icing and solving the external flow field. The numerical method is validated through simulating the NACA0012 airfoil. Then, under the rime ice condition, the mechanism and regulation are studied where the angle of attack, flight velocity, diameter of water drops, chord length of airfoil and the thickness of airfoil are different. Results show that the icing area slightly increases as the flight velocity increases with the same diameter of water drops. When the flight velocity is constant, larger diameter of water drops leads to a remarkable increase of icing area. Otherwise, a larger chord length and airfoil thickness of an airfoil results in smaller icing area respectively where the thickness of ice on stagnation point is smaller. - Author(s): Zhang Ruchen ; Bu Xueqin ; Lin Guiping ; Ge Qimo ; Qiao Xudong ; Wang Li
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(6 pp.)
A study of the design and performance calculation of the wing hot-air anti-icing system is presented. The design of the system includes the local collection efficiency calculation, the anti-icing heat load calculation, the configuration design and flow distribution calculation of the piccolo tube inside the wing antiicing cavity, structure design of the wing anti-icing cavity, which are described in detail in the paper. The performance validation of the system is conducted by the calculation of the surface temperature and the runback water on the surface. The design of the piccolo tube includes the jet hole diameter, number and distance. In order to confirm the design satisfied the need of air supply for anti-icing, the calculation of the hot-air flow distribution of the piccolo tube is performed based on the software Flowmaster, which is a one-dimensional thermal fluid simulation platform. The calculations of heat load, surface temperature and runback water are computed by user-defined functions in software FLUENT. The results show that the system designed satisfies the need of ice protection. The design method of hot-air anti-icing system proposed in this paper provide vital help for design and optimization of this system. - Author(s): Wu Yunan ; Zhang Dalin ; Chen Weijian ; Liang Qingsen ; Ma Kechang
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(6 pp.)
Nowadays, the method of evenly distributed temperature is often used to forecast the anti-icing thermal load on anti-icing surface, and results obtained by this method are often too large. In order to reduce the total anti-icing thermal load, the distribution of heating power on anti-icing surface need to be studied. In this paper, genetic algorithm has been used to optimize the distribution of heating power on electro-thermal anti-icing surface of a component for purpose of minimizing the total heating power. Then the total heating power has dropped dramatically than those where the temperature is evenly distributed on the surface. - Author(s): Li Yu ; Chen Weijian ; Yu Xiaoxiao ; Shen Hao
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(6 pp.)
Due to the fact that the traditional Messinger model cannot capture the microscopic characteristics of the ice surface well, in this paper, a random-icing model based on the behavior of individual fluid elements is established to simulate the shape and structural details of aircraft ice accretions. The random-icing model includes the ballistic part and the random-walk part. The relevant programs are written by this method, and the icing simulations on NACA 0012 airfoil under different conditions are also carried out. Finally, we compare the simulated ice shapes with the experimental values and the calculation results of CIRAMIL software based on the Messinger model. Although there are some discrepancies between experimental and predicted accretion shapes, the overall agreement is good. In particular, the ice shapes obtained by the random-icing model are rougher and their structural details are more obvious. Therefore, the random-icing model has advantages in predicting the aerodynamic characteristics of icing airfoils. - Author(s): Yu Weidong and Chang Shinan
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(6 pp.)
Droplet collision is a frequent event in the spray process of icing wind tunnel, the collision outcome can affect the droplet size and velocity distribution in the spray, and thus the performance of the icing wind tunnel. In this paper, the central collision between two equal-sized and unequal-sized water droplets is numerically investigated by using the volume of fluid (VOF) method. The reliability of the procedure is first validated by available experimental data. Then with increasing the relative velocity and keeping the relative velocity constant, the study for the effect of velocity on the central collision between two water droplets is performed. The time evolution of the collision process, the number of satellite droplets formed, the development of flow field and the variation of the kinetic and surface energy are obtained. For unequal-sized droplet collison, the spreading process of one droplet into the other is also presented. - Author(s): Xiaochuan Liu ; Xiaobin Shen ; Guiping Lin ; Zuodong Mu ; Shenli Wang
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(5 pp.)
When a plane flies under freezing weather conditions, it is prone to icing on the surface because of the impact of supercooled water droplets in the clouds. Icing of aircraft seriously endangers flight safety, and accidents caused by ice accretion occur frequently. To deal with the icing, aircraft is usually equipped with anti-icing systems. With the development of the composites, the composite electric anti-icing system has become the frontier research direction in this field. Numerical simulation method was used to study the system in this paper. The most difficult part of the simulation was to simulate the anisotropy of the composite. Fluent's user-defined scalers (UDS) was introduced to simulate the multilayer anisotropic thermal conductivity of composite materials. It is of great significance to the application of composite electric anti-icing icing system. - Author(s): Liu Ming-yang and Chang Shi-nan
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(7 pp.)
The transient heat transfer characteristics of a single circular hole jet impacting concave cylinder were obtained by thermochromic liquid crystal. In the study, the airflow Reynolds number Re, the impact distance to nozzle diameter ratio L/d and the jet impact angle α were changed. The color change process of the concave surface of the experimental part was photographed by the industrial camera. The local Nusselt number NuD distribution was calculated. The results show that the distribution of NuD for the initial phase of the jet impingement is bell type in a radial direction along the impact center. And with the impact process, the Nusselt number at the stagnation point Nus decreases gradually, where the maximum difference is 26.9%. When Re increases and L/d close to 4, the second peak is gradually obvious. As α increases, the second peak moves to the region of r / d O gradually. In addition, the linear relationship between the Re, L/d, α and Nus is obtained by linear analysis. - Author(s): Menglong Lei and Shinan Chang
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(6 pp.)
Ice accretion and water film flow on an arbitrary three-dimensional surface are the essential factors that influence the precision of ice simulation. The Myers icing model in which the water film flow equations are coupled with ice growth equations is revised and used to perform the simulation successfully. The revision mainly includes the determination of the transition from rime ice to glaze ice. The transition is determined by both its ice thickness and water flux in the revised model which can remove unreasonable ice horn and improve ice calculation result. Also, an effective numerical scheme for water film is presented. Glaze ice calculation results of a two-dimensional NACA00I2 airfoil and three-dimensional GLC-305 swept wing are presented and compared with experimental ice shape to validate its accuracy. The calculation results show major characteristics of glaze ice and agree well with the experimental results. Compared with the LEWICE results, the current method is more suitable for calculating runback ice accretion, but it has disadvantages while predicting ice horn growth.
Numerical Calculation for Water Droplet Parameters Change and Its Effect on Impingement property in Icing Wind Tunnel
Numerical study of the effect on airfoil icing with different parameters
Study of the Design and Performance Calculation of the Wing Hot-Air Anti-Icing System
Optimization for electric heating power's distribution on electro-thermal anti-icing surface
Numerical Simulation of Aircraft Icing Based on the Szilder Random-Walk model
Numerical Investigation of the Effect of Velocity on the Central Collision Between Two Water Droplets
Simulation on Electro-Thermal Anti-icing System with Composite Materials
Transient Heat Transfer Characteristics of Round Jet Impacting on Inclined Concave Cylindrical Surface Based on Thermochromic Liquid Crystal
Three-dimensional Ice Accretion Using Revised Myers Model
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- Author(s): Hong Zhang and Hong Chang
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(5 pp.)
Large aircrafts auxiliary power unit system inlet door position control system is used for controlling auxiliary power unit inlet door opening and closing on the ground and in the air. The inlet door position control design is synchronal and interactional with inlet door design, inlet door aerodynamic load analysis and inlet duct design. This paper presents a design of large aircrafts auxiliary power unit system inlet door position control. This inlet door position control subsystem is characterized with an independent controller that is separated from APU digital electronic controller and a new inlet door actuation mechanism which has the function of output torque amplification. This design of inlet door position control is applied on a large aircraft model and demonstrated. - Author(s): Xia Tianxiang ; Lu Yueliang ; Zhang Dongyu
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(6 pp.)
The Ram Air Turbine System is a commonly used airborne auxiliary power system for emergency situations. Wind power is converted to mechanical energy by turbine. Due to uncontrollability and discontinuity of wind and load, it is very important to prevent the turbine from reaching over generation or over speed. In this paper, the centrifugal pitch angle control method, as the most suitable method for RAT was first selected. Based on the moment equilibrium analysis, the rotation control method is analyzed. By using numerical computing tool, the rotation speed was calculated. Compared with the measurement in wind tunnel test, it can be found that the moment equilibrium model describes the performance of the RAT precisely. According to the sensitivity analysis, it can be found that increasing spring stiffness, spring preload and decreasing the product of inertia of the blade component can increase the stable rotation speed. Additionally, changing the damping coefficient does not affect the stable speed, but makes the rotation speed reach stability more quickly.
Design and Research of Large Aircrafts Auxiliary Power Unit System Inlet Door Position Control
Study on the rotation speed control method for Ram Air Turbine System
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- Author(s): Zhuang Cao and Xiongfeng Li
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(5 pp.)
In this paper, a Zynq SoC chip with “all programmable” feature is applied to design a miniaturized navigation controller. The controller integrates the main control module, the sensor module, image acquisition module and servo driver module through a combination of soft/ rigid printed circuit boards (PCBs). The controller utilizes the high integration feature of the Zynq chip which is equipped with dual ARM Cortex-A9 processors integrated with 28 nm Kintex-7 based programmable logic, and makes full use of the respective advantages of the ARM core and the Field Programmable Gate Array (FPGA), so the device has the advantages of high integration, rich peripheral interfaces, and application development is simple and flexible. The controller can be applied to a variety of aerospace control scenarios, such as miniature drones, microsatellites and other aircraft equipment.
A Design of Zynq-SoC-Based Miniaturized Navigation Controller
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- Author(s): Qiang Gao ; Jiawei Xiang ; Hesheng Tang
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(5 pp.)
Axial piston pumps are widely used in aircraft utility systems, especially in the hydraulic power system and the failure of this key component can result in costly downtime and even serious accident. The presence of periodical impulses in vibration signals usually indicates the occurrence of faults in axial piston pumps. Unfortunately, the incipient fault diagnosis of axial piston pump is very difficult due to the incipient fault impulses are very weak, but the nature periodical impulses are very strong both in the normal and fault axial piston pumps. Therefore, weak fault feature extraction is one of the most important tasks in the fault diagnosis of axial piston pumps. To solve this problem, we proposed a Teager energy operator (TEO) based method to extract the weak fault features from the strong vibration background. The TEO could estimate both of the kinetic and potential energy of the signal, so the Teager energy operator demodulation is more sensitive than the Hilbert demodulation and very suitable for extracting weak fault features in axial piston pumps. The simulation and experimental investigations of the roller bearing faults in axial piston pumps are implemented to illustrate the feasibility of the proposed method. - Author(s): Wanlu Jiang ; Yafei Lei ; Zhiyong Ren ; Zhengbao Li ; Sheng Zhang
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(6 pp.)
To avoid the problem of low transmission efficiency brought about by the large redundancy of the monitoring signal in hydraulic pump when remote fault diagnosis, the compression transmission of fault monitoring signal based on compressed sensing was proposed. According to compressed sensing, the original signal was sparsely represented by orthogonal basis. Then, the Gaussian matrix was used as the measurement matrix to compress the original signal, the remote transmission of the compressed data was realized by means of the Socket communication technology and TCP/IP network protocol. Moreover, the orthogonal matching pursuit algorithm was used as reconstruction algorithm to reconstruct the compression signal, the reconstruction value of original signal was obtained by the inverse sparse transformation. Finally, on the hydraulic pump fault simulation test bench, the remote fault diagnosis experiment of single slipper wear and single loose slipper are experimented. The original signal and the reconstructed signal were analyzed by Hilbert envelope demodulation. Based on power spectrum analysis, it can be found that they have the same ability for fault diagnosis. Results indicate the availability of the technology in remote fault diagnosis of hydraulic system fault. - Author(s): Xudong Shi ; Geng Zhang ; Di Chao ; Hongxu Zhao ; Xi Chen
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(5 pp.)
The airliner sealability, influenced by the closeness of cabin door, is an important factor affecting the flight safety during aircraft flights. In the aircraft cabin system, the state of the door can be judged by the value of the proximity sensor output of the door. To handle the difficulty of integrated test for airliners, taking regional airliner as studying object, the paper accomplishes the simulation of the judgment trajectory of the cabin door state for testing the inductive proximity sensor, via the cubic spline interpolation algorithm on the three-axes motion platform. Meanwhile, it analyses the ARINC429 data related to the cabin door by applying ICD database which is based on virtual instrument, and the result conduced to the test of the connection path between the proximity sensor and the PACU (Position Actuation Control Unit). Therefore, the paper significantly contributes to the integration test in the aircraft cabin door assembly plant of the regional airliner. - Author(s): Shuo Chang ; Yi Wang ; Limin Gao ; Yifan Yang
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(5 pp.)
This paper first reviews IVHM technology and summarizes current aircraft fault simulation studies briefly. Then introduces an aircraft level fault simulation for commercial aircraft health management research which include condition monitoring, fault diagnosis and prognosis. This simulated aircraft includes multiple systems linked by AFDX network. To reach this goal, unified modeling language Modelica is chosen to build models of aircraft systems. To inject simulated faults into the model, researchers first need to get a clear relation between key parameters of aircraft systems and their faults. Finally, discussion for future development of the platform is given. - Author(s): Tongyang Li ; Shaoping Wang ; Sian Shi ; Zhonghai Ma ; E. Zio
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(6 pp.)
Aliasing signals generate when two or more abrasive particles pass through an inductive debris detection sensor simultaneously, which will lead to an accumulative error for further diagnosis and prognosis of machinery equipment. The degenerate unmixing estimation technique (DUET) is an effective method for dividing aliasing signals into original sources and getting a more accurate number of the superimposed wear debris. By using the two-dimensional weighted histogram, two key parameters are estimated, which directly influences the following accuracy of source separation. To promote the precision of the parameter delay, neural networks methods including feedforward, cascade-forward, auto encoder (AE), sparse auto encoder (SAE), convolutional neural networks (CNN) are attempted and compared by using the simulative data. Different data structures are used for the testing and the result shows that the delays give the lowest mean square error (MSE) with the two-layer CNN. - Author(s): Pengju Ma ; Yan Gao ; Wen Xu ; Bo Ye ; Xuezhu Zheng
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(6 pp.)
This paper presents a tool wear monitoring method which can be applied to high-precision aero-engine parts machining. The degree of tool wear during machining is closely related to the machining accuracy. Effective state monitoring can ensure machining accuracy and provide guidelines to change tools. This paper put forward a new analysis method and monitoring program using signal of vibration and sound pressure. The process data are obtained by milling experiment. On the basis of conventional analysis, a naive bayes classifier is used to verify the validity of features which is extracted by wavelet packet analysis. The results show that the combined features of sound pressure and vibration signals can effectively indicate the degree of tool wear. - Author(s): Wei Dong ; Junmin Zhang ; Meijing Gui ; Chenguang Li
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(6 pp.)
Aviation arc fault belongs to low voltage arc fault. And it has the characteristics of short duration, low current intensity, etc. A method to identify aviation arc fault under DC power supply system based on BP neural network and wavelet packet is proposed in this paper. Firstly, the arc fault experiment platform is built to collect the current signal under normal circuit and arc condition. A base wavelet selection criteria maximum total energy to total Shannon entropy ration is used to select an appropriate wavelet for feature extraction. Then the Shannon entropy of characteristic frequency range is extracted as the characteristic quantity of arc fault. In addition, the effect of atmospheric pressure on the arc fault is also taken into account. Finally, the BP neural network optimized by Leverberg-Marquard algorithm is used to identify the arc fault. The final results show that the method proposed in this paper has a recognition rate of more than 98% for the arc fault. - Author(s): Liu Hong and Zhang Hui
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(5 pp.)
Considering the engineering application, the current development of state monitoring parameters and technology is presented in this paper, which show that prognostics health management for future aircraft has become the inevitable development, and the realization of the health management can't do without the state monitoring of the system, advanced state sensor, data processing, and fault diagnosis. And the development requirement on state monitoring technology of advanced aircraft hydraulic system is proposed to meet the integrated design of aircraft hydraulic system. - Author(s): Yang Zhang and Shaoping Wang
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(6 pp.)
In this paper, an effective approach is developed to diagnose sensor faults of fuel metering unit (FMU) control system. The accurate mathematical model of FMU is built and features of sensor fault are analyzed. To improve the accuracy of sensor diagnosis, Kalman filters are utilized to estimate the optimal outputs of dual-redundancy sensors both in the presence of process noise and measurement noise. However, the diagnosis results depend on the accuracy of system model, especially in the dynamic process. Therefore, an improved residual checking method based on a real time moving detection window is proposed to reduce the false alarm rate. In addition, the design criteria of window width and threshold value are given according to the requirements of control system. The proposed method is verified via simulation. Results show that when faults occur in a sensor, they can be accurately detected in time. Moreover, the method effectively avoids false alarm during the rising stage when the operating point changes. - Author(s): Yue Ma ; Lu Lin ; Yu Wang
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(5 pp.)
The speed sensor of the electro-mechanical transmission is the easiest to have fault, if the speed sensor breaks down, the control system of the electro-mechanical will be invalid. This paper presents a model-based method using unscented Kalman filter to diagnose the speed sensor fault. First, the mathematical model of the system is established, subsequently, the unscented Kalman filter is used to estimate the state of measurements. Moreover, the residual errors of the estimated and measured values are obtained. According to the residual errors, the fault of the system will be diagnosed. The numerical simulations demonstrate that the model-base method can diagnose the speed sensor fault accurately and in time. - Author(s): Feng Yang ; Ling Lu ; Xuemei Jiang ; Na Xiao ; Qin Wei ; Zechao Wang
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(5 pp.)
Clamps are commonly used to fix hydraulic pipelines and are generally damaged by vibration fatigue, which further induce the failure and safety accidents in hydraulic system. Therefore, it is significant for the looseness detection of incipient clamps. Commonly feature extraction is the principle step of state detection, however, it is difficult to effectively extract structural looseness features through the conventional fault detection methods due to the complexity of the fluid motion and fluid-structure coupling. Convolutional neural networks (CNN), a model of deep learning, can fully extract the characteristics from complex signals themselves and commonly used in 2D signal recognition and classification. Thus, we present a looseness detection method for clamps in hydraulic system based on the CNN and distributed Fiber Bragg Grating (FBG) sensing. A simple hydraulic pipeline testing platform is designed and realized, and the experimental data and detection results show that this method based on CNN can detect the clamps looseness well and effectively. Furthermore, the effects of different parameters of CNN are also analyzed for the detection results. - Author(s): Jun Wang ; Shaoping Wang ; Xingjian Wang ; M.M. Tomovic ; Cun Shi
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(6 pp.)
The fault-tolerant control techniques can maintain the safety of aircraft under fault conditions. Different strategies should be used to response to specific fault conditions according to the fault diagnosis information. To improve the fault-tolerant control design efficiency, this paper propose a multidimensional space based method, the flight/actuation system is divided and modeled by using the multidimensional space first, and then operator norm is used to map and quantize the fault information, finally, the decision making algorithm is designed to match the fault-tolerant control strategies to specific fault conditions. - Author(s): Cun Shi ; Shaoping Wang ; Xingjian Wang ; Jun Wang
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(6 pp.)
This paper focuses on the remaining useful life (RUL) prediction of the electro-hydrostatic actuator (EHA) highspeed pump, for which a mathematical model describing the slipper wear caused degradation is proposed. In order to improve the long-term prediction accuracy, the developed method involves the particle filtering algorithm with the state dynamic model and a measurement model to estimate the posterior probability density function for the degrading state at present time and future time. According to the failure threshold set in advance, the RUL can be obtained. The proposed model avoids making simplifying assumptions of linearity and Gaussian noise system, but provides a robust long-term prediction framework for the RUL estimation with the consideration of uncertainties. Simulation experiments and analysis have been performed to verify the effectiveness and accuracy of the proposed life prediction model. - Author(s): Liang Zhiling ; Yuan Mei ; Dong Shaopeng
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(6 pp.)
Acoustic emission (AE) technology is popularly applied to damage detection. Boundary reflection of the AE signal is believed as a reason of detecting error. The objective of this work is to propose an adaptive filter method for single source damage detection to eliminate the echo component in the acoustic emission sensor signal and obtain a pure AE signal for the subsequent damage analysis. In this paper, we present the frame model of the adaptive echo suppression system. Two adaptive filtering algorithm--normalized least mean squares (NLMS) algorithm and affine projection algorithm (APA) are applied to estimate the coefficients of the reflection path. Based on these theories, we propose an adaptive echo suppression (AES) method for AE sensor signals and verify its effectiveness by experiments. The results show that the APA-based AES method has faster convergence rate, smaller residual error and better filter performance than the NLMS-based AES method. - Author(s): Zia Ullah ; Xinhua Wang ; Yingchun Chen ; Zhang Tao ; Ju Haiyang
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(7 pp.)
This study discusses output data identification algorithms for pipeline structural defects using independent component analysis; a powerful tool for solving blind source separation (BSS) problem. Sparse like features are discovered in the three-axis magnetic field data of a pipeline use to be the hidden targeted independent sources that indicate damage information of the structure under observation. Wavelet transform algorithms are applied on the 3-axis magnetic field data. The output signals are cast into the blind source separation model where FastICA algorithms are applied on the wavelet-domain mixtures to separate them into their respective independent components. Sharp spikes are found in these independent components that clearly show the time instant of the damage occurrence. The location of the pipeline damage can be found by exploiting the (time-based) temporal information contained in the spatial signature of the recovered mixing matrix. WT-ICA method has been applied on synthetic data of a twelve degree of freedom time-varying system where damage is modeled by abrupt stiffness variation. Laboratory experiments and real world underground pipeline data were recorded and fed as mixtures in to the WT-ICA based BSS model. Results provide clear physical interpretation of the pipeline structural damages subjected to various kinds of stresses. - Author(s): Liwen Wang ; Jianwei Hu ; Jinjian Huo ; Qiang Liu ; Bing Wei ; Jie Tang ; Xudong Shi
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(5 pp.)
As the heart of aero-craft, aero-engine's performance is the most influent factors of flight safety and fuel consumption rate. When Aircraft engine works in flight, the pollutants in the air will adhere to the surface of the compressor accumulated fouling, which increases boundary layer thickness and surface roughness of gas path components wall, and seriously affects the aerodynamic performance of the engine. In this paper, the cleaning mechanism of compressor blade are analyzed in theory. Firstly, the movement characteristics of the droplet impact compressor wall are studied, and the influence of different slope angles on the splash condition is analyzed; Secondly, the shear stress - positive stress model of droplet and fouling interaction is studied. Through theoretical analysis, the optimal jet model of scale removal is obtained, which provides theoretical support for aircraft engine on-line washing. - Author(s): Hanyu Sun ; Shaoping Wang ; Xingjian Wang
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(6 pp.)
Hydraulic actuator system is one part of turbofan system. The health of this part is of great significance to the operational safety of an aero-engine. Recently with the development of a full authority digital electronic control system (FADEC), the state statistics of fuel control system's core organs have been recorded by the computer, thus provide a basis for a data driven fault diagnosis method. This paper uses simulation software AMEsim to model a hydraulic actuator loop in both normal and abnormal conditions. Then based on a data driven fault diagnosis method-principal component analysis (PCA), a PCA model is built. Finally, using the data obtained from the AMEsim model, the effectiveness of method based on PCA is verified. - Author(s): Bo Li ; Guanghan Bai ; Yan Guo ; Yun-An Zhang ; Junyong Tao
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(6 pp.)
With increasing interest in the use of unmanned aerial vehicles (UAVs), the applications of UAVs have gradually developed from single UAV to multiple UAVs. Particularly in the military field, the concept of UAV swarm has been proposed in recent years. The UAV swarm is a large number of UAVs carrying out missions in a self-organized and self-adaptive manners to achieve an overall mission objective. Despite the increasing size of the UAV swarm, little attention has been paid to the mission reliability of such system. Existing research has developed few mission reliability models for UAV swarm based on k-out-of-n structure and phase mission analysis. However, the UAV swarm is often required to carry out various missions, in which the mission reliability model based on simple k-out-of-n structure may not be appropriate. In this paper, we improved the existing mission reliability models for UAV swarm by considering limited communication range of UAVs, and/or the specific requirements by some missions. A more complex structure, namely the consecutive k-out-of-n structure is incorporated into the existing model. Thus, the UAV swarm is regarded as a consecutive k-outof-n phase mission system. Two case studies are provided to illustrate the proposed model and comparisons are made between the proposed model and the reported model using k-out-of-n structure. It is found that, by ignoring the limited communication range of UAVs, and/or the specific requirements by some missions, the reported model may overestimate the mission reliability. The proposed model can be used to support mission planning and decision making. - Author(s): Shaokang Huang ; Chao Zhang ; Shaoping Wang ; Xingjian Wang
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(5 pp.)
A sub-scale model aircraft of A380 used to verify the fault-tolerant control algorithm has been designed in this work. The similitude requirements and scaling relationships mentioned in references have been strictly followed to design the scale-model aircraft. Since it is used to verify the fault-tolerant control algorithm, the aircraft has been designed to simulate some kinds of failures during flight and could record the flight data including the control signal as well the response using the flash of the microcontroller. This paper describes how the scale-model aircraft data can be used on the full-scale airplane and takes the vertical stabilizer as an example to introduce it in detail by using CFD and wind-tunnel testing. - Author(s): Yuan Li ; Shaoping Wang ; Jian Shi ; Yixuan Geng
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(5 pp.)
A novel prediction model for the remaining useful life (RUL) of a Belleville spring based on crack propagation is proposed in this paper. The linear oscillating motor(LOM), which directly provides short stroke reciprocating motion, is extensively utilized in linear actuation systems. Belleville springs are used for mechanical resonance to counteract mover kinetic energy, and prove to be the vital component of LOM to achieve high efficiency. Failure resulting of Belleville springs from fatigue is the main failure mode of LOM in high-frequency applications. From fatigue crack initiation to complete failure, the timely and accurate prediction of Belleville spring's RUL has important significance on motor performance evaluation and flight safety especially for aircraft's Linear Electro-Hydraulic Actuator (LEHA). The Paris formula is used to describe the propagation velocity and the damage process is cumulated by the Miner rule. The RUL of different configuration and material Belleville springs can be predicted by the proposed method, which improves the design of LOM. - Author(s): Hongliang Ran ; Shaoping Wang ; Lei Fan
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(5 pp.)
In order to solve the problem of small sample size of equipment testability, a Bayesian evaluation method is proposed in this paper. Similar equipment information, equipment history information and experts' estimates are made as prior information, and their availabilities are expressed by inheritance factors, and posterior distribution of equipment testability evaluation is attained by combining with testability determination test data. This method makes both use of prior information and sample, and takes the dynamic population characteristics into consideration. At last, point estimate and lower confidence limit of testability are calculated by taking a Palletized Loading System as an example, and the results indicate that the method is validity. - Author(s): Mao Yuwen ; Yang Dongyu ; Li Ming ; Xie Changhua
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(7 pp.)
The conventional method of discrete frequency spectrum correction presents a significant error in analyzing the spectrum of extreme high frequency signal in the field of mechanical vibration and fault diagnose, which mainly results from the severe interference of negative frequency. This paper puts forward a new method of discrete frequency spectrum correction to remove the impact of negative frequency so as to improve the accuracy of extreme high frequency spectrum analysis and correction. Based on Blackman window, the periodicity of discrete spectrum and three spectrum lines near the local spectrum peak, this paper sets up a discrete spectrum correction model including both positive and negative frequency. By solving this model, the frequency, amplitude and phase correction formula can be figured out. The method of scanning with the frequency range is used to simulate and verify the spectrum correction formula. The result shows that this method can significantly undermine the impact of negative frequency on extreme high frequency signal and enhance the correction accuracy of frequency, amplitude and phase1. - Author(s): Xingjian Wang ; Jian Zhao ; Shaoping Wang ; Zhonghai Ma
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(5 pp.)
The communication proposes a method to classify the fault mode of EMAs. Traditional fault diagnosis just purposes on single components (BLDCM, ball screw, LVDT) signal analysis of EMA. Under actual circumstance, the signal detection for closed-loop electromechanical actuator system including controller and mechanical device cannot reflect single component fault. Data adopted by sensor is multidimensional and difficult to deal with. Principal component analysis(PCA) is capable to change the projection surface which decreases the amplitude of low correlation thereby reduce the data dimension. Support vector machine(SVM) is applied to data classification of less sample. This paper employs PCA to process the data adopted from mathematical model in Simulink, integrates the result and classifies the fault mode by SVM at the end. - Author(s): Pengyu Yang ; Lijing Wang ; Fengqin Sun
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(6 pp.)
In view of the problem of maintenance cost prediction of new airplane for general aircraft, a method based on the historical maintenance cost data of existing airplanes to forecast and evaluate the maintenance cost of new airplane was put forward. This method is divided into 3 steps: (1.) establishing the general aircraft structure and characteristic similarity indicators system; (2.) predicting the maintenance cost of the new airplane based on its similarity and that of the reference model; (3.) evaluating the forecast value of the maintenance cost based on the data envelopment analysis(DEA) and the adjustment value obtained in this process can be used in the initial design of the new airplane. The practical example turns out that this method can predict and evaluate the maintenance cost of the new airplane for general aircraft. - Author(s): Laixue Sun and Sian Shi
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(5 pp.)
Aiming at the current popular fault methods' disadvantages on diagnosing faults existing in electromechanical actuator, this paper presents a novel hybrid fault diagnosis approach combining Model-Based and Data-Driven. Firstly, the extended Kalman filter is used to estimate states of monitored system using available input and output variables. The residual vector corresponding to the specific fault is generated by comparing the actual measured value and estimated value. Secondly, the original accelerometer signals collected from monitored system are decomposed by EEMD and a group of the intrinsic mode functions without mode mixing are obtained. The characteristic vector is constructed by computing the energy index of every IMF. Finally, the characteristic vector is combined and acts as the training samples to train BP neural network fault classifier, therefore, the fault diagnosis is achieved. The example analysis proves that the hybrid fault diagnosis method proposed in this paper is more accurate in diagnosing direct drive EMA faults.
An incipient fault diagnosis method for axial piston pump based on the Teager energy operator
Application of compressed sensing in remote fault diagnosis of hydraulic pump
Design of an in-situ Test Equipment for the Proximity Sensor of the Aircraft Cabin Door
An Aircraft Level Fault Simulation Platform to Promote Integrated Vehicle Health Management Technology
Simulation on neural networks for DUET-based delay estimation of abrasive debris signal separation
Research on Tool Wear Monitoring of Aero-engine Parts machining
The Identification of Aviation Arc Fault Based on the BP Neural Network
State Monitoring Technology of Advanced Aircraft Hydraulic System
Dual-redundancy sensor fault diagnosis of fuel metering unit based on real-time residual window
Fault Diagnosis of the Speed Sensor of Electromechanical Transmission of the High Speed Rotorcraft
Clamps Looseness Detection of Hydraulic Pipelines Based on Convolutional Neural Network
A Multidimensional Space Based Fault-Tolerant Control System Design Method for Commercial Aircraft
Remaining useful life prediction based on particle filtering for high-speed pump in load sensing electro-hydrostatic actuator
Adaptive Echo Suppression Method Based on Affine Projection Algorithm in Acoustic Emission Detection
Blind Identification of Pipeline Damage Using Independent Component Analysis with Wavelet Transform
Study on the cleaning mechanism of the fouling of the compressor blade
Fault Diagnosis for Hydraulic Actuator of a Turbofan Control System Based on PCA
Mission-Oriented Reliability Prediction for Unmanned Aerial Vehicle Swarm using Consecutive k-out-of-n Structure
Design of a Sub-Scale Model Aircraft for Airplane Fault-tolerant Control Algorithm Testing
Crack Propagation-Based Remaining Useful Life Prediction of the Belleville Spring in Linear Oscillating Motor
A Bayesian Evaluation Method for Equipment Testability Based on Multiple Prior Information
A New Discrete Frequency Spectrum Correction Method For Extremely High Frequency Signal
Fault Diagnosis of Electromechanical Actuator Based on Principal Component Analysis and Support Vector Machine
Maintenance cost prediction and evaluation of new airplane for general aircraft
A Hybrid Fault Diagnosis Method of Electromechanical Actuator Combining Model-Based and Data-Driven
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- Author(s): Yu Chi ; Yang Chao ; Zhang Gangfeng ; Li Xiao ; Zhang Kai
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(7 pp.)
Error of airborne radar antenna servo mechanism (ARASM) was one of mostly factors to influence radar antenna precision tracking and orientation beamed. In order to analyzing precision influence magnitude by different errors, two degree freedom servo movement error model was set up in ARASM; moreover errors of different resource were analyzed. Precision influence by error was simulated and analyzed under different servo movement angles; characteristic curve of simulation experimentation show, precision influence by error was variation along with different servo angles. Error angle have imported in servo control position loop resolving measure was put forward to real time expiation. Based with application environments and actual engineering index requirements, it could handle establishing servo mechanism error model and simulation versus error controlling , distributing and synthesizing, in order to coming true radar antenna high precision by external environment apperceiving and target information obtaining. - Author(s): Zhang Tanlin ; Yang Xiaoli ; Zhao Hong
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(6 pp.)
This paper designs and makes a small pole-climbing robot, which is able to realize the self-locking in the process of climbing. The mechanical stress analysis of the robot is carried out and the mathematical model of the pole-climbing system is established. The simulation is made by Matlab/simulink..The reliability of the robot has been validated by test. On the basis of simulation, the movement of robot is controlled by PID controller embedded in Arduino board and the test of multiple climbing rods is carried out. The experimental test results show that the robot achieves the precision requirement in the established action, which provides a new method for the design of the pole-climbing robot. - Author(s): Deming Zhong ; Yukun Zhao ; Rui Sun ; Hao Wang
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(5 pp.)
System evolution, while changing a system's function, has a considerable impact on the overall safety and reliability of the system. However, recent research has not enabled an in-depth understanding of the inherent hazard of system evolution. The laws and characteristics of system evolution are not comprehensive. The principle of the hazard of system evolution must be studied to ensure the reliability and safety of the system after system evolution. For this purpose, this paper analyzes an accident case. A finite state machine and NuSMV model are established to identify the hazard transition path of each accident. The relevant initial state and target state along the transition path are identified, and the system components related to the control commands are identified along the transition path from the initial state to the target state. The relationships between the abnormal behavior of each component and the hazard state of the system are analyzed, and the principle of the evolution hazard is obtained. Finally, another accident case is used to test the system evolution hazard model. The results demonstrate that the model can accurately describe the principle of the hazard of system evolution. - Author(s): Zhuozhu Chen ; Zhenxin Hu ; Zhongxiang Shen
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(3 pp.)
This paper introduces three types of conformal low-profile end-fire antennas that can be mounted on the unmanned aerial vehicles. They include a narrow H-plane waveguide horn, a log-periodic top-hat monopole antenna, and a planar helix antenna of circular polarization. Experimental models and measurement results are presented to verify the design concepts and assess their radiation performance. These conformal, wideband, and low-profile antennas are conductor-backed, and can obtain nearly end-fire radiations over an ultra-wide bandwidth, which are potentially very useful in airborne communication applications. - Author(s): Hongjun Pang and Weijuan Zheng
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(5 pp.)
The boarding gate of an airliner is the most frequently used cabin door on an airplane. Its operability and motion characteristics directly relate to the experience of flight attendants and passengers. Focusing on a door open mechanism which includes hinge arm that has guiding role, the dynamic movement process is described by Hamilton principle, a motion model is established, and the simulation model is established in Simulink, then completing the simulation. The results verifies the theory of balance of doors open mechanism analysis. The motion and the simulation results of stress distribution show that the design of the door opening mechanism conforms to the expected design specifications. - Author(s): Dongyang Yuan ; Huajie Hong ; Maochun Du
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(6 pp.)
The rapid development of UAV has put forward more requirements in the field of airborne platform, and the existing control system has its drawbacks like complex circuit and lag of data transmission. In this paper, a new type of servo control circuit is proposed based on the FPGA and DSP dual-core control circuit. The hardware design method and software design process of the critical parts in the servo control circuit are given. Simulation and experiment results show that the design can effectively improve the timeliness as the DSP is acquiring the attitude information of platform and exchanging data with FPGA in parallel communication, and has the advantages such as high integration and function expansion. - Author(s): Liang Yan ; Yinghuang Liu ; Hongjie Hu ; Jian Shi ; Shuai Wu ; Yufeng Qu ; Liman Yang ; Xingjian Wang ; Nan Yao ; Tianyi Wang ; Longfei Zhao ; C. Gerada
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(5 pp.)
Control loading system is a device to provide pilots with rudder force feedback in flight simulator. In those systems of pilot and aircraft information interaction, control loading system gives the pilots the most intuitive information of the aircraft status. Among them, the servo motor control loading system has been used more and more because of its compact structure and superior control performance. In order to manipulate the realistic simulation of force in the load system, the model of the control loading system is proposed in this paper, and the PID controller is used to control the force servo system. The model is divided into two parts, one is the load model of the aircraft rudder to the handle, and the other is the torque model of the motor. On the basis of this, a Simulink simulation model is proposed. The simulation results show that the vibration caused by external disturbance and the delay caused by the control loading system itself have a nice inhibition effect. - Author(s): Weijuan Zheng and Hongjun Pang
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(4 pp.)
Based on the advantage of seamless integration between LMS Motion dynamics simulation module and CATIA, a prototype of the hinge arm of passenger airplane cabin door is established in CATIA, then dynamic simulation analysis is carried out in Motion. The results of Motion dynamics simulation can clearly reflect the change of Motion and force of the chain in the process of opening the door, which is consistent with the design expectation and test results, and it proves the rationality of the relevant treatment in dynamic simulation, and also demonstrates the effectiveness and convenience of LMS Motion in dynamic analysis. - Author(s): Le Yang
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(4 pp.)
The structure and working principles of airborne electromagnets were introduced and magnetic field analysis and electromagnetic attraction calculation were completed with Maxwell electromagnetic simulation software. By magnetostatic field analysis, the distribution diagrams of magnetic lines of force and magnetic induction intensity were obtained; by electromagnet attraction analysis, the electromagnet attraction was calculated and the impacts of materials, air gap and excitation on electromagnet attraction were examined, thus providing valuable reference for electromagnet optimization. - Author(s): Luo Kaixin and Fan Ying
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(6 pp.)
The integration of Global Navigation Satellite System (GNSS) and Inertial Navigation System (INS) integrate the complementary characteristics of the two systems. When the GNSS signal is outage, the INS can work alone to maintain the continuous output. Unscented Kalman Filter (UKF) is the most common means for data fusion in integrated navigation systems. However, the standard UKF will be deteriorated or even divergent if the statistic of system noise are unknown or inaccurate. A novel adaptive UKF (AUKF) with noise statistic estimator has been chosen in this paper for improving the filtering accuracy of integrated navigation systems. In the proposed algorithm, we need to find out the innovation and residual sequences, estimate and adjust the covariance matrices of the process and measurement noises online according to the covariance matching technique. Thus, we can improve the filter effect, reduce the error, and improve the precision of integrated navigation system. - Author(s): Shuting Zhang ; Liang Yan ; Bin Li ; Jian Shi ; Shuai Wu ; Yufeng Qu ; Yaoxing Shang ; Xingjian Wang ; Liman Yang ; Nan Yao ; Tianyi Wang ; Longfei Zhao ; Suokui Chang ; C. Gerada
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(5 pp.)
U-core permanent-magnet motors, which are the core component of small-sized water pumps, have high temperature rise because of their small size and concentrated heat source. This will not only affect the performance of the motor, but also cause the motor to burn out in severe cases. Therefore, it is necessary to study the thermal field of the U-core permanent-magnet motor. This paper uses the finite element software MAXWELL to calculate the loss of the motor. At the same time, the surface heat transfer coefficients of each boundary surface are calculated using an empirical formula method and an iterative method. Based on this, the finite element software ANSYS is used to calculate the motor thermal field, and a multilayer square-ring equivalent winding model is established based on the source of the calculation error to improve the calculation accuracy of the thermal field. The optimization schemes are proposed and compared for the place where the temperature rise of the motor is highest. This paper selects a reasonable optimization scheme from the temperature rise reduction ratio, lifespan, implementability and cost to provide the basis for the design and optimization of the thermal field of this type of motors. - Author(s): Xiang Zhang ; Chao Qi ; Ruoyu Tan ; Shixun Fan
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(4 pp.)
Optical micro scanners are very important instruments for ultra-high precision image stabilization and aliasing reduction in staring infrared imaging optical systems for unmanned aerial vehicle (UAV) application fields. A two-axis compliant bearing mechanism based on distribution compliance right angle flexure hinges is presented for optical micro scanners. The compliant bearing mechanism is used to support a lens as its load. It can guide the load to move translationally along two coordinate axes of a rectangular coordinate system. The mechanical topology structure of the compliant bearing mechanism is introduced. The stiffness analysis and the travel range constraint condition of the proposed compliant bearing mechanism are derived for the purpose of mechanical design. A reified prototype micro scanner equipped with the proposed compliant bearing mechanism is realized and manufactured. The experimental test result shows that the performance of the prototype compliant bearing mechanism can fulfil the expected design objective. - Author(s): Pei Tian ; Yuanheng Liu ; Shuai Zhang
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(6 pp.)
Airborne flight management system (FMS) with the ability in aspects of navigation, flight planning and guidance is one of the core subsystems in the modern avionics system, assisting the pilots in managing the entire flight and relieving the crews from the heavy workload as well. The essential role of the FMS requires the high quality performance in all-phase development especially in the function design. However, the textual design documents are utilized as media in the traditional document based methodology to be transferred to the downstream hardware/software development. One of the problems is the lack of ability to track the requirement efficiently in all lifecycle development. Another one is the ambiguity problem introduced by the textual description. In addition, the design output in terms of multi related documents may increase the inconsistence possibility when any modification is required. Therefore, it attempts to introduce the method of Model Based System Engineering (MBSE) using the system modeling language in the FMS design process to increase the trace ability and furthermore the product quality. The author then tries to use the integrated navigation function of FMS as an example to implement the new method in the design process, as the entire flight management system is a high complicated and multidiscipline covered system.
Error Modeling Analysis of Airborne Radar Antenna Servo Mechanism
Design and Analysis of Small Pole-climbing Robot
Research on a System Evolution Hazard Model
Conformal End-Fire Antennas for Unmanned Aerial Vehicles
The Dynamics Analysis and Simulation of Civil Aircraft Open Mechanism Based on Hamilton's principle
Design of Airborne Platform Control System Circuit Based on DSP and FPGA
Force modeling and control of servo motor control loading system in flight simulator
The Dynamic Simulation of Hinge Arm of Civil Aircraft Cabin Door Based on LMS Motion
A Study on Electromagnet Attraction Characteristics Based on Maxwell
Application of AUKF in GNSS/INS Integrated Navigation
Thermal Field Analysis and Optimization of the U-core Permanent-magnet Motor
Design of a Long Stroke Two-axis Compliant Bearing Mechanism for Optical Micro Scanners
MBSE based integrated navigation design for civil flight management system
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- Author(s): Dongmin Li ; Mengquan Shang ; Yanqiang Zhang ; Jia Li ; Guofang Ma
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(6 pp.)
In order to improve the performance of the current goods handling equipment for the airplane, a drilling rig is designed to meet with the complicated working conditions. Meanwhile the drilling rig can be applied in the operation of gas drainage for the high holes underground coal mine. According to the actual working conditions on the operation of gas drainage for medium or thick coal seam, the drilling rig for drilling high holes is designed based on the structure and working principle of the current drilling rig, and the hydraulic power unit is arranged separately, and 2 two-stage telescopic hydraulic cylinders are controlled respectively to adjust the height of drilling hole and the dip angle of drilling hole. Furthermore the characteristics of the supporting speed is simulated and analyzed with AMESim, thus the results show that the drilling rig can satisfy the requirement of drilling high holes and goods handling equipment for the airplane. - Author(s): Han Jianjun and Li Gen
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(5 pp.)
In this paper, the target is to optimize the laying angle and laying sequence of laminated plate structure by the improved simulated annealing algorithm. The laying angle of laminated plate is discrete variable and the simulated annealing algorithm is suitable to solve and optimize this discrete variables problem. The laminated board spreading layer was optimized by simulated annealing algorithm that uses parallel computing, introducing memory function, and setting up double threshold termination criterion. This calculation method can improve the convergence speed effectively and avoid appearing the local optimal solution in the optimization process. With the critical buckling load coefficient as the objective function, the selection of composite laminated plate laying angle as design variables, the optimal laying angle and the laying sequence are finally obtained through the improved simulated annealing algorithm. - Author(s): Lin Sun ; Songjing Li ; Lianchao Wang
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(4 pp.)
Based on the static water tow motion model of a domestic self-elevating drilling platform, the details of the truss structure such as the pile-leg and the pile-boots are studied in the present paper, so as to make it closer to the actual working conditions of the towing resistance model of the jack-up drilling platform. CFD method is used to simulate the towing resistance of a domestic self-elevating drilling platform in static water. The computing technology proposed in the paper can also be used in the aircraft industry, which also have many small cylindrical structures. - Author(s): Xibin Guo ; Jigui Zheng ; Haifeng Long ; Pengfei Li ; Zhaojing Zhang
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(4 pp.)
This paper proposes a spliced stator core structure motor permanent magnet synchronous motor analysis method, and compares the spliced structure SPM with the conventional integrated structure SPM, analyzes the influence of electromagnetic performance, temperature rise, structure and so on. - Author(s): Jing Chen ; Yuping Huang ; Yunfei Tao ; Pengfei Li ; Zhaojing Zhang
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(5 pp.)
This paper studies the modeling of biomechanical systems coupled to human and exoskeletons, and then establishes a biomechanical model of the human body. This paper also discusses how to design controllers for exoskeleton robots. The model in this article is based on a 6-DOF lower limb rehabilitation robot and a simple 3-DOF plane motion. This paper also proposes a hybrid position/force controller for a robotic rehabilitation strategy for a lower extremity after stroke. The controller has been verified by simulation of a lower extremity rehabilitation robot. - Author(s): Yaohua Hu
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(6 pp.)
The constant power speed range (CPSR) of the multi-layered interior permanent magnet (IPM) machines are investigated for the traction applications. The constant power speed range of the initial design is weak because the characteristic current is too large. Then, the structure of initial model is optimized to other two structures. Not only the constant power speed range of two optimized structures are improved by reduce the magnet volume and increase the rib width, but also can reduce the manufacturing complexity and magnet cost. The widest constant power speed range is obtained when the characteristic current equals to the rated current. Finally, a multi-layered IPM machine is manufactured to verify the FE analysis. - Author(s): Hong Zhao ; Fanbo Meng ; Tingting Wu ; Jiahe Chen
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(5 pp.)
The pipe isolation tool plays an important role in ensuring the safety of transporting oil and gas pipelines. But the life of the intelligent pipe isolation tool is also affected by the service life of the battery. Therefore, this paper based on the working principle of the pipe isolation tool and the actual working environment to improve the original hydraulic system. The accumulator absorbs the kinetic energy of the pipe isolation tool in the pipeline movement. Then the energy in the process of plugging would be released to complete the closure of plugging and save energy. First, calculate the parameters of each part of the device. Then based on the three basic equations of fluid mechanics and the calculated parameters, the mathematical model of the system is established to obtain the transfer function. Finally, the PID controller is added to improve the system performance. Simulation results verify that both energy-saving and position tracking objectives are satisfied. - Author(s): Wang Qiang ; Cao Dong-jiang ; Wang Ning
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(4 pp.)
Taking a robot with 6 degrees of freedom for research objects, the trajectory of robot is real-time planning based on the work task. The method that combines the joint space planning and the Cartesian coordinate planning is applied. Seven trajectorys involved in task are interpolating and fitting to get the smooth continuous curves of angular displacement, angular velocity and angular acceleration. The problem of robot's kinematics is solved in MATLAB to get the end effector's movement curves of x,y and z in the base coordinate system. Robot's actual motion is simulated and verified in LMS.motion. The simulation results verify that method of trajectory planning is feasible and correct in theory. - Author(s): Lin Jiansong ; Shi Hu ; Wang Haitao ; Chi Ma
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(4 pp.)
The guide holes are widely used in aircraft components machining and assembly but it is difficult to perform the visual inspection methods because of their various structural forms and inconsistent positions. To solve this problem, the paper proposes a guide holes detection method for plane parts based on binocular vision. Firstly, Harris angular points detection is used to identify the feature points of the captured images of the left and right cameras. Secondly, Scale-invariant feature transform (SIFT) algorithm is used to match the feature points, and the spatial position of the feature points is determined according to the binocular stereo vision principle. Then the space plane where the guide hole is located is found by the least squares method. Finally, the position of the camera is adjusted with the multi-axis numerical control mechanism so that the perspective projection distortion can be reduced and the detection efficiency and accuracy may be improved. - Author(s): Hong Zhao ; Jiahe Chen ; Tingting Wu ; Fanbo Meng
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(6 pp.)
As a new plugging technology, the intelligent plugging device in pipe is more and more used in the repair of oil and gas pipeline. But because of its limited energy source, it cannot be used in the plugging operation of long-distance pipeline. The hydraulic system for speed control and energy recovery is designed by using MATLAB/Simulink as the objective function of the controller. PID control and fuzzy PID control are added to hydraulic system, and the error is reduced to less than 3%. When the storage pressure is 3.80 MPa, the energy saving efficiency can reach 24.57%. The ratio increases with the increase of storage pressure. The results show that the system can accurately control the plugging speed, improve the energy utilization rate, and improve the capability of the plugging device. - Author(s): JieJi Zheng ; Ning Chen ; Chao Qi ; XiKai Jiao ; ShiXun Fan ; DaPeng Fan
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(6 pp.)
Ultrasonic motor (USM) is a basic component which utilizes the inverse piezoelectric effect and the friction interface to work. It is driven by the collective effect of parameters such as amplitude, the frequency and the phase difference of excitation signals. The output torque and speed show a strong nonlinear characteristic with excitation signals. In order to deepen the theoretical and experimental comparison of the drive characteristics of USM and master the mechanism of various factors that affect the mechanical properties of USM. This paper established a USM full parameters test system to lay a hardware foundation for the study of multi-parameter composite control algorithms. After a brief analysis of the principle of speed control of USM, this paper used the test system to test the USM. - Author(s): Xikai Jiao ; Ning Chen ; Chao Qi ; Jieji Zheng ; Shixun Fan ; DaPeng Fan
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(6 pp.)
Aiming at the test of comprehensive performance of ultrasonic motor (USM), based on the concept of rapid and efficient testing and accelerating the optimization of motor structural performance design progress, the influences of preload and excitation signal amplitude, frequency and phase on the performance of USM were analyzed. The comprehensive performance test program of USM based on Matlab was designed. The application of different types of USM showed that the program could quickly test the USM parameters and performance provide software support for rapid verification of USM performance. - Author(s): XianLiang Jiang ; Chao Qi ; ShiXun Fan ; DaPeng Fan
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(6 pp.)
The internal and external disturbance torque of the servo motor is the key factor restricting the precision of the speed servo control. In order to improve the control accuracy of DC(Direct Current) motor system, the dynamic analysis of the motor system is performed and the linear model of the motor system based on the current loop is established. The state expansion model including the disturbance torque is established based on the analysis of the nonlinear characteristics of the servo motor system. The simulation and experiment show that the disturbance observer based on the linear model of the servo motor system and its state expansion equation can realize the real-time estimation of the nonlinear disturbance torque, enhance the ability of the servo loop to restrain the disturbance, and improve the control performance of the servo motor system. - Author(s): Chen Songyue ; Wang Liang ; Yang Weixiu
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(6 pp.)
In this paper, an integrated navigation system based on MEMS-IMU/GPS is implemented through optimization of GPS information processing and Kalman filter algorithm. Low-cost IMU and GPS receivers are used with STEM32 as the core of information processing. An improved speed/position combination is adopted in this paper. Test results are presented showing the performance of the integrated MEMS GPS/inertial navigation system: This measure improves aircraft navigation accuracy and corrects the divergence more quickly. This allows integration with less errors characteristic, which is more suitable for aircrafts with low-cost, low-power, lightweight GPS chip receivers and navigation sensors. - Author(s): Ning Chen ; Chao Qi ; Jieji Zheng ; DaPeng Fan ; ShiXun Fan
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(5 pp.)
The ultrasonic motor(USM) adopts piezoelectric ceramic as energy-transducer, which is widely applied in aerospace due to its unique advantages. Its impedance characteristic can reflect the structural characteristics of USM and can be used to predict the vibration state of the stator, which is an important factor in analyzing and evaluating the evolution of motor performances. In this paper, the equivalent circuit of piezoelectric ceramics was analyzed and the admittance circle equation was derived. In response to the demand for real-time detection of voltage-current and measurement of dynamic impedance, a real-time online test platform which combines Labview with FPGA was built. In the experiment, the impedance curves were identified by the admittance circle. Parameters of the equivalent circuit were indented. Finally, the evolution rule of impedance characteristics under different voltages was studied. It was proved that the test system can measure the impedance of motor quickly and effectively. It was also verified that the resonant frequency of the ceramic decreases with the increase of the voltage, and the impedance characteristics under different voltage excitations were different. This research establishes an foundation of dynamic performance evaluation for USM in the further investigation. - Author(s): Yisen Wang ; Hu Shi ; Yanhui Xi ; Chenjing Li
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(4 pp.)
The humanoid end effector has a better performance when grabbing irregular objects. Compared to a full-drive dexterous robot hand, the underactuated gripper has a more compact structure, simpler control, and good self-adaptive ability, it can be applied to different shapes of objects. However, in some cases, improper design will lead to uneven grasping force, and it will not be able to grasp firmly or even have ejection phenomenon. So the optimization of the geometrical parameters is of great importance. In this paper, according to the designed three-degrees-of-freedom link-type underactuated manipulator, the mechanical model under grasping state is deduced by the principle of virtual work. Setting the average degree of grasping force as the optimization goal, the size and angle of pressure have been optimized by using MATLAB genetic algorithm toolbox and several suitable results have been obtained. - Author(s): Pengju Ma ; Saisai Tong ; Wen Xu ; Yan Gao ; Xuezhu Zheng ; Bo Ye
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(8 pp.)
It is very difficult to avoid the problem of tool wear or breakage during the machining of CNC machine tools. Failure to detect and stop the machine in time is likely to cause damage to the machine or workpiece. This requires the on-line monitoring of the tool state during machining. In this paper, a load-based tool wear monitoring method is proposed. The self-learning method is adopted to obtain the load range of a specific machining process, so that on-line monitoring of the subsequent same machining process can be carried out. Self-learning is mainly used to process the load signal by using the statistical algorithm (6σ algorithm), so as to obtain the upper and lower boundary of the monitoring range. The load signals in the subsequent machining process are compared with the upper and lower boundaries determined by the self-learning algorithm to determine whether the tool is worn or not. Finally, the feasibility of this method was verified by experiments. - Author(s): Xiaoyu Cui ; Shaoping Wang ; Sian Shi ; Tongyang Li ; Qing Guo
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(6 pp.)
Time-varying topologies reliability assessment for the communication network of multi-Unmanned Aircraft Vehicle (UAV) is studied. High speed of UAV causes the changing topology of the communication network. Hence, it is important to find the switching time of topologies. Aiming at designing the mobile and stable communication network, information transmission delay constraint should be considered in the reliability model. Based on queueing theory, an algorithm consisting of five steps to evaluate the performance of the communication network is presented. Finally, the effectiveness of the theoretical analysis is proved by simulations. - Author(s): A.M.E. Abdelkafi and Shaoping Wang
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(6 pp.)
This paper presents an uncalibrated image based visual servo (IBVS) scheme for automatic device. After establishing the differential drive motion model and odometry model, a visual line follower control algorithm is designed to give the appropriate pulse width modulation (PWM) control signal for differential drive of automatic vehicle based on imagine extraction, canny edge detector, center calculation and Kalman filter update. That can make the automatic vehicle move with the requested linear and angular velocities. With the image segmentation, the background captured from the front camera can be suppressed and the line center can be accurately detected. In order to decrease the noise, a discrete Kalman filter is used for tracking the line center. An error based on the difference between the image center and the line center is generated and used for steering the automatic devices follow the line. The experimental results indicate that the proposed method can realize the path tracking based on imagine. - Author(s): Zhiyuan Gao
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(5 pp.)
As an important component of metal hose, Corrugated Pipe's design will directly affect the thermal compensation and vibration of the metal hose. This Paper makes a research into finite element method (FEM) of the corrugated pipes under pressure. Based on FEM, this Paper has carried out statics properties analysis on five different thicknesses of corrugated pipe, and as a result, an optimal scheme for engineering application was determined. The determined scheme is in compliance with experimental results, proving the validity of the analytical method and can serve as guidance for the correct and rapid design.
Drilling High Holes for Drilling Rig Based on Complicated Working Conditions Underground Coal Mine
Buckling Optimization of Composite Laminated Plates based on the Simulated Annealing Algorithm
Simulation Study of Towing Resistance of Jack Up Drilling Platform Hydrostatic
Research on PMSM of spliced stator core
Hybrid Position/Force Controller for Robotic Rehabilitation of a Sitting/lying Lower Limb
Improve Constant Power Speed Range of Multi-layered Interior Permanent Mangnet Machines for Traction Application
An Energy-saving Position Control System of the Pipe Isolation Tool
The simulation on the trajectory planning of 6R robot
Study on Guide Hole Detection Method for Precise Assembly Based on Binocular Stereo Vision
Fuzzy-PID Controller Design of Energy Saving System in Pipe Isolation Tool
Research on Speed Test System of Ultrasonic Motor
Comprehensive Performance Testing Software For Ultrasonic Motor Based on Matlab
Disturbance Observer Based Controller Design of A Speed Servo System
Implementation and Performance of a GPS/INS Integrated Navigation Using MEMS Inertial Sensors
Impedance Characteristics Test of Ultrasonic motor Based on Labview and FPGA
Design and Parameter Optimization of a Three-claw Underastatctuated Gripper
A Load-based tool Wear Monitoring method for Machining process
A Delay-based Reliability Assessment for MultiUAV with Time-varying Topologies
Uncalibrated Differential Drive Visual Line Follower Automatic Vehicle
Key Parameter Design and Optimization for Aviation Corrugated Pipe with Finite Element Method