细长体飞行器自由边界热模态试验与仿真

唐晓峰; 常洪振; 何振威; 史晓鸣; 唐国安

doi:10.7527/S1000-6893.2018.22095

航空学报 >

2018 , Vol. 39 >Issue 10: 222095 - 222095

DOI: https://doi.org/10.7527/S1000-6893.2018.22095

固体力学与飞行器总体设计

细长体飞行器自由边界热模态试验与仿真

唐晓峰 ,
常洪振 ,
何振威 ,
史晓鸣 ,
唐国安

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1. 复旦大学航空航天系, 上海 200433;
2. 上海机电工程研究所, 上海 201109;
3. 北京强度环境研究所, 北京 100076

收稿日期: 2018-02-11

修回日期: 2018-04-12

网络出版日期: 2018-05-02

基金资助

上海航天科技创新基金（SAST201605）

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Thermo-modal test and simulation of spindly vehicle in free boundary conditions

TANG Xiaofeng ,
CHANG Hongzhen ,
HE Zhenwei ,
SHI Xiaoming ,
TANG Guoan

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1. Department of Aeronautics and Astronautics, Fudan University, Shanghai 200433, China;
2. Shanghai Electro-Mechanical Engineering Institute, Shanghai 201109, China;
3. Beijing Institute of Structure and Environment Engineering, Beijing 100076, China

Received date: 2018-02-11

Revised date: 2018-04-12

Online published: 2018-05-02

Supported by

Innovation Foundation of Shanghai Aerospace Science and Technology (SAST201605)

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摘要

随着耐热承载一体化材料在新型高超声速飞行器上的应用，承力结构的工作温度不断提高，各类热模态特性逐渐得到关注。针对非平面形状的细长体飞行器自由边界条件下的热模态特性开展了研究。通过研究模拟气动加热条件的圆筒形加热笼、模拟自由边界的耐高温柔性支撑、非接触激光多普勒测振、耐高温激振杆激励等试验方法，获得了细长体结构自由边界条件下随温度变化的前3阶模态变化情况。结果表明：对此类薄壁长圆筒类结构，温度升高对模态频率影响可以超过6 Hz。开展有限元仿真，并与试验取得的热模态结果的变化规律进行对比。结果表明：建立考虑温度对结构弹性模量、热应力影响的壳单元模型，能够较好地预测出前3阶模态频率在全部受热时间范围内的最大下降量，可为高超声速飞行器控制系统设计时的拉偏范围提供参考。

关键词： 气动加热模拟装置; 弹性支撑边界; 激光测振; 热模态; 模态频率

本文引用格式

唐晓峰 , 常洪振 , 何振威 , 史晓鸣 , 唐国安 . 细长体飞行器自由边界热模态试验与仿真[J]. 航空学报, 2018 , 39(10) : 222095 -222095 . DOI: 10.7527/S1000-6893.2018.22095

Abstract

As the use of more high temperature/high load durable materials in modern hypersonic vehicles requires load durable structures to work in increasingly higher temperature, much attention has been paid to thermo-modal characteristics of structures. This paper discusses the thermo-modal characteristics of a spindly vehicle with a non-planar shape in free flight boundary conditions. A cylindrical cage for aerodynamic heating simulation is studied. A free flight and flexible supporting boundary which is high temperature durable is simulated, a non-contact vibration measurement is conducted using laser Doppler, and a high temperature durable excitation pole is excited, obtaining the first 3-order modal variation of the spindly vehicle under free boundary conditions. The results show that temperature elevation can result in a 6 Hz decrease of the natural frequencies of such a thin and long cylindrical structure. A comparison of FE simulation results with test results shows that the shell element model which considers the effect of temperature on elastic module and thermo-stress of the structure can well predict the maximum decrease of the first 3-order natural frequencies in aerodynamic heating, and can thus provide some reference for the margin of the design of control system of hypersonic vehicles.

Key words： simulation device for aerodynamic heating; flexible supporting boundary; laser Doppler vibration measurement; thermo-modal; modal frequencies

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