细长体飞行器自由边界热模态试验与仿真

doi:10.7527/S1000-6893.2018.22095

Abstract

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

CLC Number:

TANG Xiaofeng, CHANG Hongzhen, HE Zhenwei, SHI Xiaoming, TANG Guoan. Thermo-modal test and simulation of spindly vehicle in free boundary conditions[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(10): 222095-222095.

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

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