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Adaptive Sliding Mode Control for Attitude Stabilization With Actuator Saturation

机译:带有执行器饱和的姿态稳定的自适应滑模控制

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摘要

The problem of attitude stabilization for a spacecraft system which is nonlinear in dynamics with inertia uncertainty and external disturbance is investigated in this paper. An adaptive law is applied to estimate the disturbances, where a sliding mode controller is designed to force the state variables of the closed-loop system to converge to the origin. Then, the spacecraft system subjected to control constraints is further considered, and another adaptive sliding mode control law is designed to achieve the attitude stabilization. No prior knowledge of inertia moment is required for both of the proposed adaptive control laws, which implies that the designed control schemes can be applied in spacecraft systems with a large parametric uncertainty existing in inertial matrix or even in unknown inertial matrix. Also, simulation results are presented to illustrate the effectiveness of the control strategies.
机译:研究了具有惯性不确定性和外部干扰的非线性动力学航天器系统的姿态稳定问题。应用自适应定律来估计干扰,其中设计了滑模控制器以强制闭环系统的状态变量收敛到原点。然后,进一步考虑受控制约束的航天器系统,设计另一种自适应滑模控制律以实现姿态稳定。对于这两个提议的自适应控制定律,都不需要先验惯性矩,这意味着所设计的控制方案可以应用于惯性矩阵甚至未知惯性矩阵中存在较大参数不确定性的航天器系统。此外,仿真结果也可以说明控制策略的有效性。

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