超声速低频大抖振气动弹性载荷试验

doi:10.7527/S1000-6893.2021.26454

Abstract

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

CLC Number:

V414

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

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