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氢动力无人机大展弦比机翼静气弹特性分析

郝帅 马铁林 甘文彪 李根

郝帅, 马铁林, 甘文彪, 等 . 氢动力无人机大展弦比机翼静气弹特性分析[J]. 北京航空航天大学学报, 2017, 43(8): 1670-1676. doi: 10.13700/j.bh.1001-5965.2016.0611
引用本文: 郝帅, 马铁林, 甘文彪, 等 . 氢动力无人机大展弦比机翼静气弹特性分析[J]. 北京航空航天大学学报, 2017, 43(8): 1670-1676. doi: 10.13700/j.bh.1001-5965.2016.0611
HAO Shuai, MA Tielin, GAN Wenbiao, et al. Static aeroelastic characteristics analysis of high-aspect-ratio wing for hydrogen-powered UAV[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(8): 1670-1676. doi: 10.13700/j.bh.1001-5965.2016.0611(in Chinese)
Citation: HAO Shuai, MA Tielin, GAN Wenbiao, et al. Static aeroelastic characteristics analysis of high-aspect-ratio wing for hydrogen-powered UAV[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(8): 1670-1676. doi: 10.13700/j.bh.1001-5965.2016.0611(in Chinese)

氢动力无人机大展弦比机翼静气弹特性分析

doi: 10.13700/j.bh.1001-5965.2016.0611
基金项目: 

航空科学基金 10200002014129002

详细信息
    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

    通讯作者:

    马铁林, E-mail: matielin@buaa.edu.cn

  • 中图分类号: V211.41;V211.47

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

Funds: 

Aeronautical Science Foundation of China 10200002014129002

More Information
  • 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。

     

  • 图 1  CFD/CSD预估-校正迭代方法流程

    Figure 1.  Procedure of CFD/CSD prediction-correction iterative method

    图 2  氢动力超长航时无人机模型

    Figure 2.  Model of hydrogen-powered ultra-long endurance UAV

    图 3  翼尖后缘挠度及机翼升力系数的收敛曲线

    Figure 3.  Convergence curves of wingtip trailing edge deflection and lift coefficient

    图 4  机翼结构变形和流场

    Figure 4.  Structure deformation and flow field of wing

    图 5  机翼后缘挠度及剖面扭转角沿展向变化曲线

    Figure 5.  Change curves of wing trailing edge deflection and twist angle along spanwise direction

    图 6  刚性与弹性机翼的纵向气动特性对比

    Figure 6.  Comparison of longitudinal aerodynamic characteristics for rigid and elastic wings

    图 7  刚性与弹性机翼的横侧向力矩特性的对比

    Figure 7.  Comparison of directional-lateral moment characteristics for rigid and elastic wings

    图 8  刚性与弹性机翼沿展向升力系数和侧力系数的对比

    Figure 8.  Comparison of lift and side force coefficient along spanwise for rigid and elastic wings

    图 9  升阻比修正结果

    Figure 9.  Correction results of lift-drag ratio

    表  1  横侧向力矩导数对比

    Table  1.   Comparison of directional-lateral moment derivatives

    机翼类型CC
    刚性机翼-0.000 35-0.000 015
    弹性机翼-0.004 9-0.000 31
    下载: 导出CSV

    表  2  不同方法的气动效能对比

    Table  2.   Comparison of aerodynamic efficiency among different methods

    方法时间/h精度精细化水平
    常用频域方法<0.1一般(预计)一般
    CFD/CSD强耦合方法46
    RC方法0.5较好较好
    下载: 导出CSV
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出版历程
  • 收稿日期:  2016-07-20
  • 录用日期:  2016-10-21
  • 网络出版日期:  2017-08-20

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