Rigid-flexible coupling dynamic modelling and thermally induced vibration analysis for a flexible spacecraft

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Journal of Vibration and Shock ›› 2016, Vol. 35 ›› Issue (24) : 79-83.

SUN Shu-peng, WANG Wei, DUAN Xiao

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Abstract

The rigid-flexible coupling dynamic model for a flexible spacecraft with large solar panels which are modeled by honeycomb panels is established by using the Hamiltonian principle. The effects of rigid-flexible coupling nonlinear terms in the dynamic model and the parameters of the flexible spacecraft on the natural characteristics and thermally induced vibration of the system are investigated. The numeric simulation results show that the frequencies of the system increase as the moment of inertia for the rigid hub of the flexible spacecraft decrease, and there is a particular honeycomb core height to solar panel thickness ratio such that the frequency taking the maximum. The rigid-flexible coupling nonlinear terms do not affect the quasi-static part of the thermally induced response of the flexible spacecraft. However, they make the amplitude of vibration part increase and the system frequency change. When the reciprocal of the thermal time constant of the system is close to the fundamental frequency, the amplitude of thermally induced vibration is maximum. The conclusions provided theoretical guidance for the spacecraft design.

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thermally induced vibration / solar panel / rigid-flexible coupling / honeycomb panel / flexible spacecraft

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SUN Shu-peng, WANG Wei, DUAN Xiao. Rigid-flexible coupling dynamic modelling and thermally induced vibration analysis for a flexible spacecraft[J]. Journal of Vibration and Shock, 2016, 35(24): 79-83

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