This paper investigates a novel adaptive attitude controller design for rigid microsatellite based on feedback linearization approach, in which an accurate attitude pointing is required within a strict power limitation for space environment. The control strategy is performed to guarantee the stability of the satellite attitude under the effect of uncertain actuator parameters such as torque magnitude error and misalignment. The controller estimates the total torque fault through an observer in order to provide a reliable attitude control during the satellite manoeuvre. The stability of the closed-loop dynamic of the designed control law is proven via Lyapunov analysis. Finally, a comparative study with the well-known controllers from the literature is examined through numerical simulations to demonstrate the feasibility and effectiveness of the proposed control method.

本文研究了一种基于反馈线性化方法的刚性微卫星自适应姿态控制器的新颖设计，其中在空间环境的严格功率限制内需要精确的姿态指向。执行控制策略以确保在不确定的执行器参数（例如，扭矩大小误差和未对准）的影响下，卫星姿态的稳定性。控制器通过观察者估算总扭矩故障，以便在卫星操纵过程中提供可靠的姿态控制。通过Lyapunov分析证明了所设计控制律的闭环动力学的稳定性。最后，