Abstract A new orbit-attitude-vibration coupled dynamic model of the tethered solar power satellite (Tethered SPS) is established based on absolute nodal coordinate formulation. The Hamilton’s equation of the system is derived by introducing generalized momentum through Legendre transformation. The correctness of the proposed model is verified by an example. The dynamic characteristics of the Tethered SPS are studied using the symplectic Runge-Kutta method. Simulation results show that the orbital radius and the total energy of the system are well preserved. The attitude of the system is unstable when the mass of the bus system is small. However, the attitude stability is dependent on some other parameters of the system, which requires further studies. It is also found that the average tether force/deformation can be roughly estimated by simplifying the solar panel as a particle. The proposed model can be used to study the orbit-attitude-vibration coupled dynamics and control problems.

中文翻译：

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系留太阳能卫星轨道-姿态-振动耦合动力学

摘要 基于绝对节点坐标公式，建立了一种新的系留太阳能卫星(Tethered SPS)轨道-姿态-振动耦合动力学模型。系统的哈密顿方程是通过勒让德变换引入广义动量推导出来的。通过实例验证了所提出模型的正确性。使用辛 Runge-Kutta 方法研究了系留 SPS 的动态特性。仿真结果表明，系统的轨道半径和总能量得到了很好的保留。当总线系统的质量较小时，系统的姿态不稳定。然而，姿态稳定性取决于系统的一些其他参数，这需要进一步研究。还发现可以通过将太阳能电池板简化为粒子来粗略估计平均系绳力/变形。该模型可用于研究轨道-姿态-振动耦合动力学和控制问题。