航空学报 > 2014, Vol. 35 Issue (6): 1581-1591   doi: 10.7527/S1000-6893.2013.0529

利于冬季飞行的太阳能飞机构型研究

马东立, 包文卓, 乔宇航   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100191
  • 收稿日期:2013-09-09 修回日期:2014-01-22 出版日期:2014-06-25 发布日期:2014-02-26
  • 通讯作者: 马东立,Tel.:010-82338635 E-mail:madongli@buaa.edu.cn E-mail:madongli@buaa.edu.cn
  • 作者简介:马东立男,博士,教授。主要研究方向:飞行器总体设计、飞行力学、隐身技术研究。Tel:010-82338635 E-mail:madongli@buaa.edu.cn包文卓男,硕士研究生。主要研究方向:飞行器总体设计。Tel:010-82338635 E-mail:baowenzhuo@sina.com;乔宇航男,博士研究生。主要研究方向:飞行器总体设计。Tel:010-82338635 E-mail:qyuhangxp@hotmail.com
  • 基金资助:

    国家“863”计划(2012AA7052002)

Study of Solar-powered Aircraft Configuration Beneficial to Winter Flight

MA Dongli, BAO Wenzhuo, QIAO Yuhang   

  1. School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China
  • Received:2013-09-09 Revised:2014-01-22 Online:2014-06-25 Published:2014-02-26
  • Supported by:

    National High-tech Research and Development Program of China(2012AA7052202)

摘要:

针对冬季太阳辐射强度较弱的问题,提出并研究了一种新型太阳能飞机构型。概述了太阳能飞机的总体构型,建立了太阳辐射和能源动力系统模型,对飞机的气动、能量、质量及机翼最优偏转角等特性进行了分析,给出了适用于该构型太阳能飞机的总体参数设计方法,并对构型设计参数进行了研究。结果表明:机翼偏转角的存在可有效提高太阳能飞机所接收的太阳辐射能量。综合考虑太阳辐射能量和推进系统质量,机翼最优偏转角在7.4°~9.5°之间,其随时刻变化;端板最优展弦比为5左右,端板与机翼的最优面积比为0.09,端板最大许用升力系数的最优值为1.1。新构型太阳能飞机总面积比常规构型减小44.2%,其优势明显。

关键词: 太阳能飞机, 飞机构型, 太阳辐射, 超长航时, 机翼面积

Abstract:

To address the problem of weak solar radiation intensity in winter, a new solar-powered aircraft configuration is put forward and studied. The general solar-powered aircraft configuration is summarized. The models of solar radiation intensity and energy power system are built. Aircraft characteristics of aerodynamic, power, weight, and optimal wing's deflection angle are analyzed, and a general-parameters design method for the new solar-powered aircraft configuration is introduced which is used to study the design parameters of the aircraft configuration. The results show that the existence of the wing's deflection angle can effectively improve the solar radiation intensity that the aircraft receives. The optimal wing's deflection angle is between 7.4°and 9.5°, changing by time. The optimal aspect ratio of the end-plates is around 5. The optimal area ratio of the end-plates to wing is 0.09. The optimal maximum allowable lift coefficient of the end-plates is 1.1. The new configuration solar-powered aircraft can decrease the total area by 44.2% as compared with the normal solar-powered aircraft configuration, which shows its obvious superiority.

Key words: solar-powered aircraft, aircraft configuration, solar radiation, ultra-long endurance, wing area

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