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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2021, Vol. 42 ›› Issue (3): 623972-623972.doi: 10.7527/S1000-6893.2020.23972

• Special Topic of Electric Aircraft • Previous Articles     Next Articles

Design and test of two-seater electric aircraft

FAN Zhenwei1,2, YANG Fengtian1,2, LI Yadong1,2, XIANG Song1,2, ZHAO Weiping1   

  1. 1. Key Laboratory of General Aviation, Shenyang Aerospace University, Shenyang 110136, China;
    2. Liaoning General Aviation Research Institute, Shenyang 110136, China
  • Received:2020-03-14 Revised:2020-04-02 Published:2020-07-27
  • Supported by:
    Projects of Education Department of Liaoning Province (JYT19004, JYT19022, JYT2020161, JYT2020162)

Abstract: Shenyang Aerospace University has been committed to the development of new energy electric aircraft. The development project of a type of two-seater light electric aircraft was approved and started in June 2012, using a 40 kW rare earth permanent magnet synchronous DC motor as the power source. With all-composite body and leaf spring landing gear structure, a cruise lift to drag ratio of 24.1, take-off weight of 500 kg, a maximum flight velocity of 160 km/h, a cruise velocity of 110 km/h, the electric aircraft has the characteristics of zero emission, low noise, low operation cost and easy operation and maintenance. According to the CAAC CCAR-21 and the American ASTM standard, the electric aircraft type design approval TDA and the production certification PC are completed.

Key words: electric aircraft, two-seater, lithium battery, aerodynamics, flight test

CLC Number: