ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Thermal vibration test on wing structure of high-speed flight vehicle using TARMA model method
Received date: 2014-09-30
Revised date: 2015-03-02
Online published: 2015-03-25
Supported by
Ministry Level Project
It is important to investigate the thermal modal test of wing structure in the design and securely flight of the modern high-speed flight vehicle.The mathematical model of modal parameters identification of time-varying thermal structure, which is validated in a numerical example, is founded by time-dependent auto regression moving average (TARMA) model method.The wing structure thermal modal test system is designed by combining the ground vibration test system with the transient thermal environment simulation system.The vibration displacement of test structure is measured under random excitation signal.The change of the first four modal frequencies with heating time identified by TARMA model, that is founded by vibration displacement and shaking force measured by thermal modal test system, are well agreed with the results of numerical computation, and the error between them is less than 5%.In addition, the identification results under uniform temperature distribution thermal structure are well agreed with the results of the numerical computation, too.The reason of modal frequencies of time varying thermal structure changing with the heating time is discovered, by comparing the identification results under transient temperature field with those under uniform temperature field.The modal frequencies are influenced by structure material degraded and uniform thermal stress in structure together.
LIU Hao , LI Xiaodong , YANG Wenqi , SUN Xiasheng . Thermal vibration test on wing structure of high-speed flight vehicle using TARMA model method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015 , 36(7) : 2225 -2235 . DOI: 10.7527/S1000-6893.2015.0057
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