一种精确鲁棒的刚体航天器特征轴旋转控制策略(英文)

特征轴旋转表征了两个方位之间的最短角路径,通常被看做是一种拟最小时间的快速姿态机动策略。本文在动力学方程中考虑了外部扰动和系统参数不确定性,基于时变滑模控制技术(TVSMC)研究了刚体航天器特征轴旋转的鲁棒控制问题。首先,通过一个TVSMC算法揭示了所提出鲁棒特征轴旋转策略的主要特点,并且证明了全局滑模的特点和闭环系统的稳定性,给出了特征轴旋转的必要条件。然后,为了抑制全局抖振,提高控制精度,提出了一种基于扰动观测器的时变滑模控制(DOTVSMC)算法。其中,采用边界层方法来削弱抖振并设计了扰动观测器来补偿不期望的影响。在航天器的姿态表征参数选择上,采用了没有冗余性的修正罗德里格斯参数(MRP)。最后,采用数值仿真来验证提出方法的有效性,并采用调宽调频(PWPF)技术来调制开关推力器。

A Precise and Robust Control Strategy for Rigid Spacecraft Eigenaxis Rotation

Eigenaxis rotation is generally regarded as a near-minimum time strategy for rapid attitude maneuver due to its constitution of the shortest angular path between two orientations. In this paper, the robust control problem of rigid spacecraft eigenaxis rotation is investigated via time-varying sliding mode control (TVSMC) technique. Both external disturbance and parameter variation are taken into account. Major features of this robust eigenaxis rotation strategy are first demonstrated by a TVSMC algorithm. Global sliding phase is proved as well as the closed-loop system stability. Additionally, the necessary condition for eigenaxis rotation is provided. Subsequently, to suppress the global chattering and improve the control accuracy, a disturbance observer-based time-varying sliding mode control (DOTVSMC) algorithm is presented, where the boundary layer approach is used to soften the chattering and a disturbance observer is designed to attenuate undesired effect. The spacecraft attitude is represented by modified Rodrigues parameter (MRP) for the non-redundancy. Finally, a numerical simulation is employed to illustrate the effectiveness of the proposed strategy, where the pulse-width pulse-frequency (PWPF) technique is utilized to modulate the on-off thrusters.