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研究在轨服务航天器逼近与捕获目标航天器的相对轨道姿态耦合动力学建模问题。考虑航天器姿态与对接位置的运动耦合,建立目标运行在任意轨道下的相对轨道姿态耦合动力学模型,并对模型中的运动耦合进行深入分析。设计一种非线性的输出反馈姿态控制律,将建立耦合动力学模型与CW方程进行仿真比较,验证轨道与姿态的运动耦合对两航天器对接点之间相对位置的运动影响。
The problem of orbital attitude-coupled dynamics modeling of orbiting spacecraft approach or capture target spacecraft is studied. Considering the kinematic coupling between the spacecraft attitude and the docking position, the coupled orbit attitude coupling dynamics model with the target running under any orbit is established, and the kinematic coupling in the model is further analyzed. A nonlinear output feedback attitude control law is designed. The coupling dynamics model and the CW equation are simulated and compared to verify the influence of orbital-pose kinematic coupling on the relative position between the two spacecraft docking joints.