Control design for PMM-based starter generator system for More Electric Aircraft

Yeoh, Seang Shen; Gao, Fei; Bozhko, Serhiy; Asher, G.M.

doi:10.1109/epe.2014.6910893

Cited by 25 publications

(24 citation statements)

References 15 publications

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“…The dynamic equations for PMSG in the dq frame are as follows [36]: In this example a surface-mounted PMSG is used, thus the machine inductances in the d-axis and q-axis …”

Section: Effect On Pmsg-based Systemmentioning

confidence: 99%

An Improved Voltage Compensation Approach in A Droop-Controlled DC Power System for the More Electric Aircraft

Gao

Bozhko

Asher

et al. 2015

IEEE Trans. Power Electron.

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137

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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.For more information, please contact eprints@nottingham.ac.uk 1 Abstract-This paper proposes an improved voltage regulation method in multi-source based DC electrical power system in the more electric aircraft. The proposed approach, which can be used in terrestrial DC microgrids as well, effectively improves the load sharing accuracy under high droop gain circumstance with consideration of cable impedance. Since no extra communication line and controllers are required, it is easily implemented and also increases the system modularity and reliability. By using the proposed approach the DC transmission losses can be reduced and system stability is not deteriorated for normal and fault scenarios. In this paper optimal droop gain settings are investigated and the selection of individual droop gains as well as the proportional power sharing ratio has been described. Experimental results validate the effectiveness of the proposed method.Index Terms-DC power system, droop control, load sharing, voltage deviation, transmission losses.

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“…The dynamic equations for PMSG in the dq frame are as follows [36]: In this example a surface-mounted PMSG is used, thus the machine inductances in the d-axis and q-axis …”

Section: Effect On Pmsg-based Systemmentioning

confidence: 99%

An Improved Voltage Compensation Approach in A Droop-Controlled DC Power System for the More Electric Aircraft

Gao

Bozhko

Asher

et al. 2015

IEEE Trans. Power Electron.

Self Cite

137

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“…The controlled variables are regulated using well known PI based controllers. A dynamic limiter is present which determines the limit for iq * based on id * and im using the current limit equation [11]: Figure 2. Control scheme of generator system.…”

Section: Generator Mode Control Schemementioning

confidence: 99%

“…The FW controller has been designed and its stability analyzed in starter mode [11]. Since the initial speed controller for starter mode is switched to Edc controller, the stability aspects may change and could affect the performance of the FW controller in generator mode.…”

Section: Flux Weakening Controller Designmentioning

confidence: 99%

“…The high frequency voltage signal and the subsequent demodulation of high frequency stator current make it possible to achieve sensor-less operation of fulltorque from zero speed to ignition speed. Detailed control design of the PMM-based S/G has been studied in [11] and [12]. These papers consider regulation of DC link current during generating mode to accommodate droop control for possible parallel operation of multisource aircraft power system.…”

Section: Introductionmentioning

confidence: 99%

“…The paper shall cover the control design of the S/G system in generator mode only. More information on starter mode control can be found in [11] and [12].…”

Section: Introductionmentioning

confidence: 99%

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

Yin

Bozhko

Yeoh

2016

SAE Int. J. Aerosp.

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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.

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Sliding mode control of permanent magnet generator system based on improved exponential rate reaching law

Huang

Zhang

Han

et al. 2020

IET Electric Power Applications

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This study focuses on the improvement in the transient performance of DC‐link voltage for a permanent magnet generator (PMG) system. Based on the vector control theory and double closed‐loop control, the sliding mode control (SMC) method with the improved exponential rate reaching law (IERRL) is proposed in the voltage loop of the PMG system. The switching surface is designed with an integral term of state variable to suppress chattering and increase response speed. In addition, the IERRL that combines the concept of constant‐proportional rate reaching law and exponential reaching law is proposed to further suppress chattering and eliminate steady‐state tracking error of DC‐link voltage. A detailed analysis of control law, system stability, reaching time, and chattering on switching surfaces are presented as well. The SMC method with IERRL improves the transient performance under sudden load changing occasion and eliminates the steady‐state tracking error of DC‐link voltage. Simulation and experimental results verify the effectiveness of the proposed method.

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Control design for PMM-based starter generator system for More Electric Aircraft

Cited by 25 publications

References 15 publications

An Improved Voltage Compensation Approach in A Droop-Controlled DC Power System for the More Electric Aircraft

An Improved Voltage Compensation Approach in A Droop-Controlled DC Power System for the More Electric Aircraft

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

Sliding mode control of permanent magnet generator system based on improved exponential rate reaching law

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