超声速低频大抖振气动弹性载荷试验

doi:10.7527/S1000-6893.2021.26454

天问一号着陆火星专栏

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超声速低频大抖振气动弹性载荷试验

侯英昱¹, 李齐², 季辰¹, 刘子强¹

1. 中国航天空气动力技术研究院, 北京 100074;
2. 北京空间飞行器总体设计部, 北京 100094

收稿日期:2021-09-28 修回日期:2021-10-26 出版日期:2022-03-15 发布日期:2021-11-23
通讯作者: 侯英昱 E-mail:249049538@qq.com
基金资助:
火星探测重大工程项目

Experimental design of aeroelastic load with supersonic low frequency and large buffeting

HOU Yingyu¹, LI Qi², JI Chen¹, LIU Ziqiang¹

1. China Aerospace Aerodynamic Technology Research Institute, Beijing 100074, China;
2. Beijing Institue of Spacecraft System Engineering, Beijing 100094, China

Received:2021-09-28 Revised:2021-10-26 Online:2022-03-15 Published:2021-11-23
Supported by:
Major Mars Exploration Project

摘要/Abstract

摘要： 为研究超声速条件下结构在流场中所受振动特性和载荷特征，并且确定飞行器的结构安全，需进行相应模型的载荷试验。但是由于风洞尺寸和相似比等因素的限制，在弹性模型设计、激励、标定、测量等各个方面存在较大困难。论文介绍了该试验弹性模型载荷试验过程中涉及的火星进入舱模型动载荷试验技术、小尺度结构载荷测量技术、结构体内部传动激振技术。给出这3项技术的设计需求、传统试验方法的不足、技术改进和技术实施效果，并利用上述3项技术建立了火星进入舱模型的静动态载荷试验平台，完成了风洞试验。试验结果显示所述试验技术可有效完成对飞行器的载荷测量，测量结果真实可信，具有可行性和有效性。此外还证明了在试验工况下，飞行器结构不会发生振动发散的现象，结构不会发生破坏。

关键词: 弹性模型, 超声速风洞试验, 气动弹性试验, 配平翼, 载荷

Abstract: In order to study the vibration and load characteristics of the structure in the flow field under supersonic conditions and determine the structural safety of the aircraft, the load test of the corresponding model is needed.However, due to the limitations of wind tunnel size and similarity ratio, there are great difficulties in elastic model design, excitation, calibration, measurement and so on.This paper introduces the dynamic load test technology of Mars entry module model, small-scale structural load measurement technology and internal transmission excitation technology involved in the elastic model load test of the test.The design requirements of these three technologies, the shortcomings of traditional test methods, technical implementation scheme and technical implementation effect are introduced.The static and dynamic load test platform of Mars entry module model is established by using the above three technologies, and the wind tunnel test is completed.The test results show that the above test technology can effectively complete the load measurement of aircraft, and the measurement results are authentic, feasible and effective.In addition, it is also proved that under the test conditions, the aircraft structure will not have the phenomenon of vibration divergence and the structure will not be damaged.

Key words: elastic model, supersonic wind tunnel test, aeroelastic test, balance wing, load

中图分类号:

V414

侯英昱, 李齐, 季辰, 刘子强. 超声速低频大抖振气动弹性载荷试验[J]. 航空学报, 2022, 43(3): 626454-626454.

HOU Yingyu, LI Qi, JI Chen, LIU Ziqiang. Experimental design of aeroelastic load with supersonic low frequency and large buffeting[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 626454-626454.

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超声速低频大抖振气动弹性载荷试验

Experimental design of aeroelastic load with supersonic low frequency and large buffeting

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