一种模型独立的拟欧拉轴航天器大角度姿态机动

刚性航天器初始姿态捕获 ,要求从任意初始状态机动到角速度要求为零的指定状态。本文基于姿态偏差四元数和瞬时旋转轴偏离欧拉轴程度信息反馈 ,设计了一种拟欧拉轴旋转姿态捕获控制规律。对于刚体的任意初始状态 ,角速度可能不平行于欧拉轴。为减少瞬时旋转轴的偏移程度 ,将初始角速度分解为平行和垂直欧拉轴的两个分量 ,控制器在初始阶段尽快消除垂直角速度分量 ,随后进行拟欧拉旋转机动。最后给出了分析的仿真结果

Model Independent Near Eigenaxis Rotation for Move-to-rest Spacecraft Large Angle Maneuver

This paper presents the problem of reorientating a rigid spacecraft from arbitrary initial conditions to prescribed conditions with zero angular velocity. The control law is based on attitude quaternion feedback and another information that describes the deviation from the eigenaxis feedback. For arbitrary initial states, the angular velocity may not parallel to the eigenaxis. In order to reduce the deviation, the initial angular velocity is decomposed into a parallel and a perpendicular component to eigenaxis, and the control law eliminates the perpendicular component at the start phase as quickly as possible. Then a near eigenaxis rotation occurs at the rest phase. At last, the analysis is verified by simulation.