北京航空航天大学学报 ›› 2016, Vol. 42 ›› Issue (7): 1479-1485.doi: 10.13700/j.bh.1001-5965.2015.0464

• 论文 • 上一篇    下一篇

利于减少配平损失的太阳能飞机构型设计

阙建锋, 王维军, 吴宇   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100083
  • 收稿日期:2015-07-13 出版日期:2016-07-20 发布日期:2016-07-29
  • 通讯作者: 王维军,Tel.: 010-82317519 E-mail: wangwj@buaa.edu.cn E-mail:wangwj@buaa.edu.cn
  • 作者简介:阙建锋 男 硕士研究生。主要研究方向:太阳能飞机概念设计和建模仿真。E-mail: jfq7708@126.com;王维军 男,博士,副教授。主要研究方向:飞行动力学仿真与控制、微小型飞行器设计试验。Tel.: 010-82317519 E-mail: wangwj@buaa.edu.cn

Design of solar-powered aircraft configuration for reducing trim loss

QUE Jianfeng, WANG Weijun, WU Yu   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2015-07-13 Online:2016-07-20 Published:2016-07-29

摘要: 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。

关键词: 太阳能飞机, 气动配平损失, 概念设计, 构型设计参数, 平飞需用功率

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.

Key words: solar-powered aircraft, aerodynamic trim loss, concept design, configuration design parameters, flying power required

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