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access icon openaccess Design and simulation of the accumulator for servomechanisms of launch vehicle

This is an open access article published by the IET under the Creative Commons Attribution License (http://creativecommons.org/licenses/by/3.0/)
Received 06/02/2020, Accepted 22/05/2020, Published 11/08/2020

The accumulator is a crucial component of the hydraulic power for servomechanisms of the launch vehicle, which has a significant effect on the performance and the mass power. Traditional design methods are mostly based on empirical formulas, which do not meet the requirements of the fine design of aerospace products. The physical model, the mathematical model of the accumulator and joint simulation model of the energy and the control loop are established, and parameters satisfying the extreme flight operation profiles are obtained, including the discharge volume, charge volume and charge pressure. The flight data of third-stage servomechanisms of the Long March 3 series Launch Vehicle were analysed, which is consistent with the simulation data, indicating that the accumulator has exerted the maximum capability in the extreme flight condition, and the maximum mass power has been realised.

Inspec keywords: vehicle dynamics; design engineering; servomechanisms; aerospace control; space vehicles; aerospace simulation

Other keywords: extreme flight operation profiles; mathematical model; charge volume; joint simulation model; flight data; hydraulic power; aerospace products; third-stage servomechanisms; empirical formulas; Long March 3 series Launch Vehicle; physical model; charge pressure; fine design; discharge volume; mass power; accumulator; simulation data; extreme flight condition

Subjects: Aerospace engineering computing; Vehicle mechanics; Aerospace industry; Aerospace control; Aerospace testing and simulation

References

    1. 1)
      • 7. Edwards, J.W.: ‘Analysis on electrohydraulic aircraft control-surface servo and comparison with test results’, Nasa Technical Note. NASA TN D-6928, August 1972.
    2. 2)
      • 1. Caye, P., Descamps, D., Ariane, V.: ‘Thrust vector control development Status’. AIAA 94–3069, 30th AIAA/ASME/SAE/ASEE Joint Propulsion Conf., Indianapolis, IN, USA, June 27–29 1994.
    3. 3)
      • 6. Wang, Z.L.: ‘Hydraulic control system’ (Beihang University Press, People's Republic of China, 1987).
    4. 4)
      • 4. Green, W.L.: ‘Accumulator time constants and the ‘INdex’ method: some comparisons based on experimental data’. National Conf. on Fluid Power, USA, 1979.
    5. 5)
      • 10. Yin, C.: ‘Study on servomechanism's control algorithm optimization to suppress load resonance’, China Aerospace Science and Technology Corporation, 2012.
    6. 6)
      • 9. Zhao, S., Jing, G.: ‘Study on the design of the accumulator and oil-tank for the servomechanism using numerical opitimization’. The Servo-Forum Papers of the Chang Kong company in 2005, Beijing, People's Republic of China, 2005.
    7. 7)
      • 8. Liu, R.: ‘Nonlinear Control of Electro-hydraulic Servo-Systems: Theory and Experiment’, M.S. Degree Thesis, University of Illinois at Urbana-Champaign, 1998.
    8. 8)
      • 3. Lei, T.: ‘New hydraulic engineering manual’ (Beijing Institute of Technology University Press, People's Republic of China, 1998).
    9. 9)
      • 5. Merritt, H.E.: ‘Hydraulic control systems’ (Wiley, New York, 1967).
    10. 10)
      • 2. Zhao, S., Zhao, Y., Jiang, Q.Y., et al: ‘The 2nd stage servomechanism system for liquid oxygen-kerosene manned launch vehicle’, Manned Spaceflight, 2012, 18, (5), pp. 1–7.
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