Comparison and analysis of new high power density axial flux permanent magnet machine for electric propulsion aircraft

被引:0
|
作者
Gao H. [1 ]
Zhang Z. [1 ]
Wang C. [1 ]
Xue H. [1 ]
Liu Y. [1 ]
机构
[1] Center for More-Electric-Aircraft Power System, Nanjing University of Aeronautics and Astronautics, Nanjing
来源
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2022年 / 43卷 / 05期
基金
中国国家自然科学基金;
关键词
Axial flux permanent magnet machine; Electric propulsion aircraft; Ironless stator machine; Power density; Slotless machine;
D O I
10.7527/S1000-6893.2021.25229
中图分类号
学科分类号
摘要
To achieve high power density and high efficiency of the motor in electric propulsion aircraft, this paper proposes a slotless Axial Flux Permanent Magnet (AFPM) machine, which inherits high efficiency of ironless stator AFPM machine, and achieves higher power output capability. Firstly, topologies of three kinds of AFPM machines are described, including ironless stator AFPM machine, slotless AFPM machine, and Yokeless Armature and Segmented Armature (YASA) AFPM machine. Then, the winding factor, torque output capability and loss distribution of the three kinds of machines are analyzed, and the mechanisms of losses of the machines are also studied. When used as the aircraft propulsion machine, the three machines are compared in terms of electromagnetic characteristics. The results show that the slotless AFPM machine proposed has the advantages of high power density and high efficiency, and is suitable for the electric propulsion aircraft. Finally, the prototype of a 50 kW ironless stator AFPM machine is developed, and the experimental results verify the correctness of the theory and simulation analysis method. © 2022, Beihang University Aerospace Knowledge Press. All right reserved.
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  • [1] SARLIOGLU B, MORRIS C T., More electric aircraft: Review, challenges, and opportunities for commercial transport aircraft, IEEE Transactions on Transportation Electrification, 1, 1, pp. 54-64, (2015)
  • [2] WEIMER J., Past, present and future of aircraft electrical power systems, 39th Aerospace Sciences Meeting and Exhibit, (2001)
  • [3] BRADLEY M K, DRONEY C K., Subsonic ultra green aircraft research:Phase I final report, (2011)
  • [4] DAVIES K, NORMAN P, JONES C, Et al., A review of turboelectric distributed propulsion technologies for N+3 aircraft electrical systems, 2013 48th International Universities' Power Engineering Conference (UPEC), (2013)
  • [5] FELDER J, KIM H, BROWN G., Turboelectric distributed propulsion engine cycle analysis for hybrid-wing-body aircraft, 47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, (2009)
  • [6] BROWN G., Weights and efficiencies of electric components of a turboelectric aircraft propulsion system, 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, (2011)
  • [7] NALIANDA D, SINGH R., Turbo-electric distributed propulsion opportunities, benefits and challenges, Aircraft Engineering and Aerospace Technology, 86, 6, pp. 543-549, (2014)
  • [8] KONG X H, ZHANG Z R, LU J W, Et al., Review of electric power system of distributed electric propulsion aircraft, Acta Aeronautica et Astronautica Sinica, 39, 1, (2018)
  • [9] AGRAWAL S, BANERJEE A, BEACH R., Brushless doubly-fed reluctance machine drive for turbo-electric distributed propulsion systems, 2018 AIAA/IEEE Electric Aircraft Technologies Symposium, pp. 139-155, (2018)
  • [10] ANDERSON A D, RENNER N J, WANG Y Y, Et al., System weight comparison of electric machine topologies for electric aircraft propulsion, 2018 AIAA/IEEE Electric Aircraft Technologies Symposium, (2018)