摘要
以追踪星对非合作失效卫星的超近距离巡视为背景,对基于参考轨迹的失效卫星相对位姿建模与控制进行研究。根据非合作失效卫星在空间定轴慢旋的特性,通过在失效卫星表面确定一个兴趣区域,建立便于相对位姿动力学模型设计的参考坐标系与兴趣坐标系,从而便于位置与姿态2个方面的参考轨迹指令的实时计算;基于Hill方程和姿态动力学模型,推导基于非合作目标表面参考点的近似耦合相对位姿动力学模型;在此基础上,设计相对位姿耦合控制方法,并进行Simulink仿真实验验证。仿真结果表明:基于参考轨迹推导的相对位姿动力学模型简洁有效,设计的位姿耦合控制方法使系统具有较高的控制精度,相对位置控制精度为0.1 m,相对姿态控制精度为0.15。
The super-close distance perambulation of the chaser satellite with respect to the non-cooperative satellite is taken as the background. Research is conducted on the modeling and control of the relative position and attitude for the non-cooperative failed satellite based on the reference trajectory. According to the fixed-axis, slowly rotating characteristics of the non-cooperative satellite, an interest field is determined on the surface of the failed satellite, and the reference frame and interest frame are established for the model design of the relative position and attitude. It＇s convenient for the real-time calculation of the reference trajectory instruction. According to Hill equation and attitude dynamic model, an approximate coupling relative position and attitude dynamic model is proposed based on the reference point of the non-cooperative target. On this basis, the relative position and attitude coupled control method is designed, and the simulation is verified. The simulation analysis has showed that the proposed relative position and attitude dynamic model based on the reference trajectory is simple and valid, and the designed coupled control method has high control precision whose control precision of relative position is 0.1 meter and relative attitude is 0.15 degree.
出处
《兵工自动化》
2013年第4期15-20,共6页
Ordnance Industry Automation
基金
国家自然基金(61203197)
江苏省高校青蓝工程资助项目
江苏高校优势学科建设工程资助项目
中央高校基本科研业务费专项资金资助
南京航空航天大学基本科研业务费专项科研项目资助
关键词
失效卫星
超近距离巡视
参考轨迹
相对位姿
建模与控制
failed satellites
super-close distance perambulation
reference trajectory
relative position and attitude
modeling and control
