Performance analysis derivative based updating method

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The design of satellite structures is bound to be highly conservative.The finite element model updating technology of satellite structures was proposed to solve this problem.In addition, the physical test period is long and expensive; this hinders the development of the satellite industry.The finite element simulation technology can conduct a comprehensive dynamic analysis of a product and obtain its response under various conditions.In particular, when a spacecraft launches and reenters the atmosphere at high speeds, the resulting random high-frequency vibrations and noise vibrations within the fairing can produce a mean square response acceleration of up to 50 g for the satellite structure.Therefore, it is necessary to carry out comprehensive dynamic analysis before launch to obtain accurate response prediction results for flight safety and good operation [10–12].Honeycomb sandwich panel structures comprise 80–90% of the shell and shell structure of spacecraft [8, 9].

A satellite is subjected to an extremely harsh vibration shock and noise environment during use and launch.For these reasons, it is quite difficult to establish an accurate and reasonable finite element model.There is error between finite element analysis results and experimental values.The simulation and test acceleration response of the modified finite element model of a honeycomb panel are compared under the two conditions of sine sweep and random vibration.The acceleration response curves of reference points are consistent, and amplitude and frequency errors are within acceptable limits.

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