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中文摘要：
针对近距离航天器的相对轨道提出了一种鲁棒自适应控制律。在追踪星本体坐标系中考虑航天器的相对运动。首先,在转动惯量未知的情形下提出了自适应控制律,保证系统的全局渐近稳定性。其次,将两星地心引力加速度之差作为干扰加速度,并假设干扰有未知上界,对自适应控制律进行修正,提出了鲁棒自适应律,使得系统是全局一致最终有界稳定的。控制律的设计不需要绝对轨道信息,适用于任意轨道。对航天器编队飞行和空间交会两种情形分别进行了仿真分析,结果表明所设计的控制律是合理有效的。
英文摘要：
The problem of relative orbit motion for nearby spacecrafts is studied in this paper. The relative orbit motion is described in the body frame of a chaser spacecraft. In the case with unknown inertia matrix of the chaser spacecraft,an adaptive control law to make the system globally asymptotically stable is proposed. Under the assumption that the disturbances are unknown yet bounded. Taking the differential acceleration of gravity between two spacecrafts as disturbing acceleration,a robust adaptive law is proposed via modification of the adaptive control law,thus guaranteeing the system to be globally uniformly bounded stable. No orbital parameters are needed in the control law design. Simulation results of a leader-follower spacecraft formation flight and rendezvous are provided to show the effectiveness of proposed control algorithm .
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