基 于 几 何 力 学 的 类 平 板 式 卫 星 全 耦 合 动 力 学

This paper focuses on the structural characteristics of plate-type satellites and establishes attitude-orbit-structure coupling dynamic equations in the Euler-Lagrange and Hamilton forms using Lagrange mechanics and Hamil⁃ ton mechanics on the Lie group，respectively. This method simultaneously considers the coupling effect among the at⁃ titude，orbit，and plate structure appendage vibrations of spacecraft in orbit. The vibration phenomenon of the plate structure appendage is approximated by a single degree of freedom torsion spring model. This description method can easily describe the vibration phenomenon through Lie group tools. On the other hand，the dynamic equations derived from the perspectives of Lagrange geometry and Hamilton geometry are global and coordinate free. In addition，the establishment of the system dynamics model considers the time-varying characteristics of the satellite center of mass，making it more accurate. The effectiveness of this modeling method is verified using numerical examples. Through simulation comparison with the rigid model，the attitude-orbit-structure coupling effect of the quasi-plate satellite under excitation is analyzed. Results show that the model has good stability and can accurately predict the dynamic re⁃ sponse of the quasi flat satellite in orbit under excitation.