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Volume 42 Issue 7
Jul.  2016
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Journal of Beijing University of Aeronautics and Astronautics  > 2016  >  42(7): 1479-1485.
QUE Jianfeng, WANG Weijun, WU Yuet al. Design of solar-powered aircraft configuration for reducing trim loss[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(7): 1479-1485. doi: 10.13700/j.bh.1001-5965.2015.0464(in Chinese)
Citation: QUE Jianfeng, WANG Weijun, WU Yuet al. Design of solar-powered aircraft configuration for reducing trim loss[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(7): 1479-1485. doi: 10.13700/j.bh.1001-5965.2015.0464(in Chinese)
shu

Design of solar-powered aircraft configuration for reducing trim loss

doi: 10.13700/j.bh.1001-5965.2015.0464

  • School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • Received Date: 13 Jul 2015
  • Publish Date: 20 Jul 2016
    Abstract
  • The solar-powered aircraft with the static stability generally uses tail trim, which causes the trim loss. To address the problem of the aerodynamic trim loss, a new solar-powered aircraft configuration called "T" configuration was put forward. The general solar-powered aircraft configuration was summarized. The trimming principle by lowing center of gravity in the state of cruise flight was analyzed. The models of energy balance and mass analysis were built. A concept design method which is suitable for the new solar-powered aircraft configuration was introduced, and then the design parameters of the aircraft configuration were optimized. The results show that the solar-powered aircraft of "T" configuration not only has static stability, but also reduces the trim loss. In the state of cruise flight, the solar-powered aircraft of "T" configuration can decrease the flying power required in unit area by 6.2% compared with the normal solar-powered aircraft, which shows obvious application effect.

     

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