利于减少配平损失的太阳能飞机构型设计

针对具有静稳定性的太阳能飞机一般采用尾翼配平造成气动配平损失的问题，提出了一种“T”构型太阳能飞机。概述该太阳能飞机的总体构型，分析该构型飞机巡航状态下降低重心的自配平原理，建立能量平衡和质量分析模型，给出适合于该构型太阳能飞机的概念设计方法，并优化构型设计参数。结果表明,“T”构型太阳能飞机不仅具有静稳定性，还降低了配平损失。在巡航状态下,“T”构型太阳能飞机单位面积平飞需用功率比常规构型太阳能飞机减少了6.2%，具有明显的应用效果。 

Design of solar-powered aircraft configuration for reducing trim loss

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.