TY - JOUR
T1 - Design of solar-powered aircraft configuration for reducing trim loss
AU - Que, Jianfeng
AU - Wang, Weijun
AU - Wu, Yu
N1 - Publisher Copyright:
© 2016, Editorial Board of JBUAA. All right reserved.
PY - 2016/7/1
Y1 - 2016/7/1
N2 - 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.
AB - 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.
KW - Aerodynamic trim loss
KW - Concept design
KW - Configuration design parameters
KW - Flying power required
KW - Solar-powered aircraft
UR - https://www.scopus.com/pages/publications/84980315373
U2 - 10.13700/j.bh.1001-5965.2015.0464
DO - 10.13700/j.bh.1001-5965.2015.0464
M3 - 文章
AN - SCOPUS:84980315373
SN - 1001-5965
VL - 42
SP - 1479
EP - 1485
JO - Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics
JF - Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics
IS - 7
ER -