Control Design for PMM-Based Generator Fed by Active Front-End Rectifier in More-Electric Aircraft

Abstract

(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.

Variable-Voltage Bus Concept for Aircraft Electrical Power System

“…Similar control scheme was introduced in [15] with the use of droop based bus voltage controller focusing on its design and stability analysis. Classic bus voltage control was used in [18], [19] and [20]. Their control schemes seemed sufficient for the priorities mentioned earlier, however an alternative control scheme has to be considered to introduce the "voltage wild" concept.…”

Modulation Limit Based Control Strategy for More Electric Aircraft Generator System

“…Overall, the structure enables voltage and current limits through the |vs| controller and the dynamic limit respectively. This control scheme has been extensively covered in [5,9,10] and notably, it has been reported that the |vs| controller has some stability limits and hence is needed to be designed carefully. The current is limited by the dynamic limit and there is a potential to exceed the m limit (2) due to the |vs| controller error corrective action.…”

“…Since the stator current is the control variable for this loop, hence the plant can be derived from the linearised current limit equation (9). Using the equations ( 5) to ( 13), the is plant can be derived to be: ( ) q s q so q i i x s x s x i i y s y s y i…”