导航

ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2018, Vol. 39 ›› Issue (10): 222095-222095.doi: 10.7527/S1000-6893.2018.22095

• Solid Mechanics and Vehicle Conceptual Design • Previous Articles     Next Articles

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

TANG Xiaofeng1,2, CHANG Hongzhen3, HE Zhenwei3, SHI Xiaoming2, TANG Guoan1   

  1. 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:2018-02-11 Revised:2018-04-12 Online:2018-10-15 Published:2018-05-02
  • Supported by:
    Innovation Foundation of Shanghai Aerospace Science and Technology (SAST201605)

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: