近距离星间相对姿轨耦合动力学建模与控制  

Coupled Relative Attitude-Orbit Dynamics and Control of Anear Satellites

作　　者：苏晏[1,2] 黎康[1,2] 

机构地区：[1]北京控制工程研究所,北京100190 [2]空间智能控制技术重点实验室,北京100190

出　　处：《空间控制技术与应用》2014年第4期20-25,共6页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(61304232)

摘　　要：针对在轨服务过程中近距离星间相对位置以及相对姿态精确控制的问题,考虑相对姿态与相对轨道之间的耦合作用,建立星间相对姿轨耦合动力学模型.提出编队星相对基准星进行接近绕飞的任务需求,给出相对姿态以及相对轨道的期望状态.设计相对姿态轨道联合控制算法对相对姿态和轨道进行联合控制.仿真结果表明,所设计的控制算法能够很好地抑制相对姿态与相对轨道的相互影响作用,最终实现编队星对基准星的精确指向绕飞运动.For on-orbit autonomous servicing, the relative position and attitude of anear satellites should be controlled accurately. Considering the coupled relation between the relative position and attitude, cou- pled attitude-orbit dynamics model is established. The deputy satellite is required to close to and finally move around the chief satellite in the task. The expected relative position and attitude are discussed. A control law combined the relative position and attitude is proposed to realize the task requirement. The numerical simulation results show that the control law can overcome the disturbance effects between the relative position and attitude, and finally ensures that the deputy satellite points to and moves around thechief satellite precisely.

关 键 词：相对姿轨耦合动力学 目标指向需求 Lyapunov最小 最大控制 

分 类 号：V448[航空宇航科学与技术—飞行器设计]