卫星快速绕飞轨迹设计与制导

快速绕飞在航天器近距离观测、空间目标识别与侦察、在轨服务与应急情况处理活动中具有重要应用。首先建立了适用于目标航天器运行在圆轨道或椭圆轨道的相对运动状态转移矩阵;然后,推导了采用多脉冲控制方法实现与目标航天器共面和异面快速绕飞、进入绕飞和退出绕飞的轨迹设计与制导的模型和算法;最后,分析了绕飞过程速度脉冲需求与绕飞参数的关系。仿真计算结果表明所提出的快速绕飞轨迹设计模型和制导算法可以用于对圆轨道或椭圆轨道目标航天器的共面或异面快速绕飞。

A General Method of Trajectory Design and Guidance for Fast Satellite Circumnavigation

Fast circumnavigation is an enabling technology for future on-orbit servicing and operations such as on-orbit inspection and observation in proximity,space objects identification,reconnaissance and surveillance,on-orbit maintenance and emergent situation settlement.In this paper a state transition matrix is introduced,which could be applied to the cases of a target satellite in circular orbit or in elliptical orbit.The state transition matrix is further used to develop the trajectory design and guidance algorithms for enter into circumnavigation,fast circumnavigation and exit circumnavigation based on multiple-impulse maneuver method.Finally the relationships between some circumnavigation parameters and impulse required for fast circumnavigation are analyzed.Simulation works are carried out and the results indicate the proposed methodology of trajectory design and guidance for fast satellite circumnavigation can be used for coplanar or non-coplanar trajectory design and guidance with a target spacecraft in circular or elliptical orbit.