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

doi:10.13700/j.bh.1001-5965.2016.0611

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

郝帅¹,
马铁林^2, ,,
甘文彪²,
李根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

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
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- 被引次数: 0
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

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

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

Funds:

Aeronautical Science Foundation of China 10200002014129002

More Information

Corresponding author: MA Tielin, E-mail: matielin@buaa.edu.cn

摘要

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。
- 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.
- hydrogen-powered UAV /
- high-aspect-ratio wing /
- static aeroelastics /
- fluid-structure coupled /
- aerodynamic correction

HTML全文

图 1 CFD/CSD预估-校正迭代方法流程

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

下载: 全尺寸图片幻灯片

图 2 氢动力超长航时无人机模型

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

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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

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图 4 机翼结构变形和流场

Figure 4. Structure deformation and flow field of wing

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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

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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

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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

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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

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图 9 升阻比修正结果

Figure 9. Correction results of lift-drag ratio

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表 1 横侧向力矩导数对比

Table 1. Comparison of directional-lateral moment derivatives

机翼类型 C_lβ C_nβ

刚性机翼 -0.000 35 -0.000 015

弹性机翼 -0.004 9 -0.000 31

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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 好好

RC方法 0.5 较好较好

下载: 导出CSV

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