北京航空航天大学学报 ›› 2017, Vol. 43 ›› Issue (8): 1670-1676.doi: 10.13700/j.bh.1001-5965.2016.0611

• 论文 • 上一篇    下一篇

氢动力无人机大展弦比机翼静气弹特性分析

郝帅1, 马铁林2, 甘文彪2, 李根1   

  1. 1. 北京航空航天大学航空科学与工程学院, 北京 100083;
    2. 北京航空航天大学无人系统研究院, 北京 100083
  • 收稿日期:2016-07-20 修回日期:2016-10-21 出版日期:2017-08-20 发布日期:2016-11-16
  • 通讯作者: 马铁林 E-mail:matielin@buaa.edu.cn
  • 作者简介:郝帅,男,硕士研究生。主要研究方向:飞行器总体设计、流固耦合技术、多学科优化技术;马铁林,男,博士,高级工程师。主要研究方向:飞行器总体设计、无人机技术、多学科优化技术;甘文彪,男,博士,讲师。主要研究方向:飞行器总体设计、飞行器气动设计、计算流体力学;李根,男,硕士研究生。主要研究方向:飞行器总体设计、飞行器气动设计、飞行汽车技术。
  • 基金资助:
    航空科学基金(10200002014129002)

Static aeroelastic characteristics analysis of high-aspect-ratio wing for hydrogen-powered UAV

HAO Shuai1, MA Tielin2, GAN Wenbiao2, LI Gen1   

  1. 1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
    2. Research Institute of Unmanned Systems, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2016-07-20 Revised:2016-10-21 Online:2017-08-20 Published:2016-11-16
  • Supported by:
    Aeronautical Science Foundation of China (10200002014129002)

摘要: 以氢动力超长航时无人机(UAV)为背景,针对其大展弦比轻质复合材料机翼,采用强耦合方法求解了几何非线性变形下的静气弹特性,对比了弹性机翼与刚性机翼的气动性能,并在此基础上,给出了一种刚性机翼的弹性气动力修正方法。结果表明:相比刚性机翼,弹性机翼巡航状态下的升阻比降低3.2%,滚转力矩导数和偏航力矩导数显著增大,对飞机的气动性能产生不利影响;基于刚性计算结果,对大展弦比机翼进行气动修正,是一种有效的大展弦比轻质机翼气动分析思路。

关键词: 氢动力无人机, 大展弦比机翼, 静气动弹性, 流固耦合, 气动修正

Abstract: Based on hydrogen-powered ultra-long endurance unmanned aerial vehicle (UAV), nonlinear static aeroelastic characteristics were analyzed by the strong-coupled method for its high-aspect-ratio light composite wing. The aerodynamic comparison of rigid and elastic (aeroelastic deformation) wing was investigated. And then, an aerodynamic correction method, based on the result of the rigid wing, was applied to the elastic wing. The results show that the lift-drag ratio of the elastic wing reduces by 3.2% (compared to the rigid wing), and roll and yaw moments significantly increases to the disadvantage of aerodynamic performance. The aerodynamic correction based on rigid computation results is an efficient aerodynamic analysis strategy for high-aspect-ratio light composite wing.

Key words: hydrogen-powered UAV, high-aspect-ratio wing, static aeroelastics, fluid-structure coupled, aerodynamic correction

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