Control and optimisation of hybrid electric propulsion system for light aircraft
- Author(s): Al Savvaris 1 ; Ye Xie 1 ; Letian Wang 1 ; Siqi Wang 1 ; Antonios Tsourdos 1
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View affiliations
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Affiliations:
1:
Fluid Mechanics and Computational Science , Cranfield University , Cranfield, Bedford , UK
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Affiliations:
1:
Fluid Mechanics and Computational Science , Cranfield University , Cranfield, Bedford , UK
- Source:
Volume 2018, Issue 13,
2018,
p.
478 – 483
DOI: 10.1049/joe.2018.0013 , Online ISSN 2051-3305
The growing economical and environmental pressures have accelerated the research and development of hybrid electric power technology in order to increase aircraft performance and reduce the operating and maintenance costs. There has been a big increase in the electrical power rating on new aircraft entering into service. This study gives an overview of the design and development of a hybrid electric propulsion system for light General Aviation aircraft. The theoretical and practical challenges are reviewed and elaborated firstly. The system architecture design is based on a parallel configuration. The ground test of the developed hardware-in-the-loop system is presented based on a test flight mission.
Inspec keywords: hybrid electric vehicles; design engineering; research and development; aircraft testing; electric propulsion; cost reduction; aircraft control; optimisation; aerospace propulsion; environmental economics
Other keywords: optimisation; electrical power rating; system architecture design; parallel configuration; operating cost reduction; maintenance cost reduction; hybrid electric propulsion system control; research and development; light general aviation aircraft performance; test flight mission; economical-environmental pressures; hardware-in-the-loop system testing
Subjects: Optimisation; Aerospace control; Aerospace industry; Engines; Aerospace propulsion; Economics; Testing
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