吸气式高超声速飞行器热气动弹性研究进展

杨超; 赵黄达; 吴志刚

doi:10.13700/j.bh.1001-5965.2019.0120

吸气式高超声速飞行器热气动弹性研究进展

doi: 10.13700/j.bh.1001-5965.2019.0120

杨超^{1, 2},
赵黄达^{1, 2},
吴志刚^{1, 2, ,}

1.
北京航空航天大学航空科学与工程学院, 北京 100083
2.
航空器先进设计技术工业和信息化部重点实验室, 北京 100083

详细信息

作者简介:
杨超  男, 博士, 教授, 博士生导师。主要研究方向:飞行器设计、气动弹性力学、飞行动力学

赵黄达  男, 博士研究生。主要研究方向:气动弹性力学

吴志刚  男, 博士, 副教授, 博士生导师。主要研究方向:气动弹性力学与主动控制

通讯作者:
吴志刚, E-mail: wuzhigang@buaa.edu.cn

中图分类号: V211.47
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- 文章访问数: 1138
- HTML全文浏览量: 150
- PDF下载量: 566
- 被引次数: 0
出版历程
- 收稿日期: 2019-03-22
- 录用日期: 2019-05-27
- 网络出版日期: 2019-10-20

Research progress of aerothermoelasticity of air-breathing hypersonic vehicles

YANG Chao^{1, 2},
ZHAO Huangda^{1, 2},
WU Zhigang^{1, 2
, ,}

1.
School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China
2.
Key Laboratory of Aircraft Advanced Design Technology, Ministry of Industry and Information Technology, Beijing 100083, China

More Information

Corresponding author: WU Zhigang, E-mail: wuzhigang@buaa.edu.cn

摘要

摘要:
吸气式高超声速飞行器是当前航空航天领域研究的热点，该类飞行器通常使用超燃冲压发动机作为推进系统，并采用一体化设计方案，带来了一系列的气动弹性问题。首先阐述了吸气式高超声速飞行器机体/发动机一体化建模研究进展；随后介绍了热气动弹性/推进耦合、控制系统耦合以及不确定性分析等方面的热气动弹性动力学研究进展，并对相关热气动弹性试验研究进行了分析；最后对吸气式高超声速飞行器的热气动弹性问题提出了若干研究建议。
- 气动弹性 /
- 一体化设计 /
- 超燃冲压发动机 /
- 吸气式高超声速飞行器 /
- 控制系统耦合
Abstract:
Nowadays the air-breathing hypersonic vehicles are focused on by the researchers of aeronautics and astronautics. This type of vehicle usually uses a scramjet engine and an integrated design method, which brings a series of aeroelastic problems. This paper first describes the research progress of integrated airframe/engine modeling of air-breathing hypersonic vehicles. Then the research status of aerothermoelastic dynamics is introduced from the aspects of aerothermoelastic/propulsion coupling, control system coupling and uncertainty analysis. The related aerothermoelastic experimental research is analyzed. Finally, several suggestions for the study of aerothermoelastic problems of air-breathing hypersonic vehicles are proposed.
- aeroelasticity /
- integrated design /
- scramjet engine /
- air-breathing hypersonic vehicles /
- control system coupling

HTML全文

图 1 超燃冲压发动机解析模型^[4]

Figure 1. Scramjet engine analytical model^[4]

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图 2 MASIV程序使用的发动机模型^[6]

Figure 2. Engine model used in MASIV^[6]

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图 3 试验装置示意图及MASIV程序计算模型^[8]

Figure 3. Experimental device schematic and MASIV calculation model^[8]

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图 4 压力分布结果对比^[8]

Figure 4. Comparison of pressure distribution results^[8]

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图 5 飞行器几何外形^[4]

Figure 5. Vehicle geometry^[4]

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图 6 弹性机体模型^[4]

Figure 6. Elastic vehicle model^[4]

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图 7 吸气式高超声速飞行器几何模型^[23]

Figure 7. Geometric model of air-breathing hypersonic vehicle^[23]

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图 8 内部体积分布示意图^[24]

Figure 8. Internal volume layout^[24]

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图 9 飞行中第一阶模态振型演变情况^[24]

Figure 9. Evolution of first-order mode shape during flight^[24]

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图 10 高超声速飞行器等轴视图^[11]

Figure 10. Isometric view of hypersonic vehicle^[11]

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图 11 典型的吸气式高超声速飞行器三视图(非比例绘图)^[26]

Figure 11. Three-sided view of a typical air-breathing hypersonic vehicle (figures not to scale)^[26]

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图 12 吸气式高超声速飞行器三维视图^[28]

Figure 12. Air-breathing hypersonic vehicles 3D view^[28]

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图 13 气动弹性模型中使用的结构模态振型及真空下频率^[14]

Figure 13. Structural mode shapes and in-vacuo frequencies used in aeroelastic model^[14]

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图 14 法向力随迎角变化^[14]

Figure 14. Normal force variation with angle of attack^[14]

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图 15 一阶弯曲模态的演变过程^[35]

Figure 15. Evolution of first-order bending mode^[35]

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图 16 考虑气动加热和燃料消耗的系统极点/零点演变过程^[35]

Figure 16. Evolution of system poles/zeros considering aerodynamic heating and fuel consumption^[35]

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图 17 不同机身弯曲刚度下的飞行包线^[36]

Figure 17. Flight envelopes under different bending stiffness of fuselage^[36]

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图 18 开环零极点随机身刚度减小的变化^[36]

Figure 18. Open-loop zero-pole variation with stiffness reduction of fuselage^[36]

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图 19 复平面中的特征值分布^[26]

Figure 19. Eigenvalue distribution in complex plane^[26]

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图 20 系统开环传递函数的Nyquist曲线对比(K=2.5)^[45]

Figure 20. Comparison of system open-loop transfer function Nyquist diagram when K=2.5^[45]

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图 21 纵向动力学模态复值特征根不确定范围^[56]

Figure 21. Complex eigenvalue uncertainty range of longitudinal dynamic modes^[56]

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图 22 高超声速风洞中的翼面及颤振试验装置^[60]

Figure 22. Wing model and flutter testing apparatus in hypersonic wind tunnel^[60]

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图 23 试验模型与支撑机构^[63]

Figure 23. Test model and support mechanism^[63]

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图 24 模拟气动力加载的导弹气动伺服弹性地面试验测试系统^[70]

Figure 24. Missile aeroservoelastic ground test system with simulated aerodynamic load^[70]

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