卫星特征面悬停的相对轨道控制策略

Relative orbit control for specific hovering of satellite

卫星近距离操作任务通常需要维持机动卫星与目标卫星特征面的相对位置,目前针对卫星的悬停研究少有考虑地球不规则摄动和推力饱和因素.针对特征面悬停中目标卫星自旋和未知外界摄动干扰的问题,设计了基于滑模理论的轨道维持策略.使用自适应估计的方法估计了未知外界摄动上界,并将其引入控制律中.在控制律设计中引入了可变参数调节推力,以避免饱和并加快误差收敛.以CW方程(clohessyGwiltshireequations,CW)模型为标称模型设计控制律,在地球J2项摄动模型下进行仿真校验.仿真结果表明:控制策略具有较好的鲁棒性和较快的收敛速度.

Space proximity operation missions often require to maintain the relative position between the satellite with the specific surface of the target.Recent studies rarely consider the perturbation from Earth's irregular shape and thrust saturation.To deal with the problems of unknown perturbation and the spin of target satellite,a robust maintain strategy was proposed based on slide mode control theory.The upper boundary of the perturbation acceleration was estimated adaptively and introduced to the control law.By introducing variable coefficients into the control law,thrust saturation was avoided and the convergence of error was expedited.The nominal trajectory was designed in CW equation,and the control law was implemented in the natural model of Earth J2 model.In the numerical simulation,the tracking error converged in a short period and the control law showed good robustness.