Finite Element Anaysis Of Solar Panel On Man-Made Satellite

Solar panel on man-made satellite is a kind of flimsy structure in aerospace. Dynamic behavior of solar panel is an important factor necessary to be taken into consideration in satellite control, in that it is relatively complex and directly influences the orientation stability of the satellite.Main works done in the dissertation are listed as follows: The concept of joining element is introduced and a Finite Element dynamic model of Combined Panels (CP) is established.The linear modes of the CP are also analyzed,which provides dynamic parameters for vibration control of solar panels. A rigid-flexible coupling dynamic model of satellite-CP system is established and, according to this model, the dynamic response of the CP under impactive load is calculated.A nonlinear Finite Element dynamic equation of solar panel is deduced on the basis of nonlinear strain-displacement relationship and the nonlinear amplitude-frequency characteristic of the solar panel is analyzed.The time-displacement responses of solar panel's free vibration and compulsive vibration are also calculated with Subsection Method and Least Squares-Optimization Method respectively.In addition, a computer program used to solve large-scale rigid-flexible coupling dynamic equations and visualize calculated results is developed.