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(2016) Control design for PMM-based generator fed by active front-end rectifier in more-electric aircraft. SAE International Journal of Aerospace, 9 (1). pp. 23-29. ISSN 1946-3901 Access from the University of Nottingham repository: http://eprints.nottingham.ac.uk/44373/1/Control%20Design%20for%20PMM-based %20Generator%20fed%20by%20Active%20Front-End%20Rectifier%20in%20More-Electric %20Aircraft.pdf Copyright and reuse:The Nottingham ePrints service makes this work by researchers of the University of Nottingham available open access under the following conditions. This article is made available under the University of Nottingham End User licence and may be reused according to the conditions of the licence. For more details see: http://eprints.nottingham.ac.uk/end_user_agreement.pdf A note on versions:The version presented here may differ from the published version or from the version of record. If you wish to cite this item you are advised to consult the publisher's version. Please see the repository url above for details on accessing the published version and note that access may require a subscription. AbstractThe future aircraft electrical power system is expected to be more efficient, safer, simpler in servicing and easier in maintenance. As a result, many existing hydraulic and pneumatic power driven systems are being replaced by their electrical counterparts. This trend is known as a move towards the More-Electric Aircraft (MEA). As a result, a large number of new electrical loads have been introduced in order to power many primary functions including actuation, de-icing, cabin airconditioning, and engine start. Therefore electric power generation systems have a key role in supporting this technological trend. Advances in modern power electronics allow the concept of starter/generator (S/G) which enables electrical engine start and power generation using the same electrical machine. This results in substantial improvements in power density and reduced overall weight. One of the potential S/G solutions is to employ a permanent magnet machine (PMM) controlled by active front-end rectifier (AFE). Operation of the PMM as a generator at wide range of speed that is dictated by the engine and electrical loads connected to the aircraft bus require careful design of the controllers. Corresponding plant models are derived and verified with simulations using developed models in Matlab/Simulink. The relevant controllers are designed based on the derived plants and operating points. The controllers are tested with Simulink models and experimentally using a scaled prototype of the investigated generator system.

This paper deals with a novel control system design of More Electric Full Authorized Digital Electronic Control (MEFADEC) on the more electric aircraft. On the base of the analysis of the power management of MEFADEC system, the power of the more electric aircraft is also the vital platform to be considered. The definition of microgrid is introduced in the power management of the MEFADEC. The control law of the MEFADEC is the main course of this paper and some simulations are done to verify the design of the control system using Matlab/Simulink. The paper concludes that a closed loop speed control law of MEFADEC could meet the requirements of the original purpose and the outcome of the simulations have confirmed this. Some further research of the control of MEFADEC are needed to be done and even some practical experiments should get involved in this institution in the future.