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Robust dynamic output feedback control for attitude stabilization of spacecraft with nonlinear perturbations

机译：具有非线性扰动的航天器姿态稳定的动态输出反馈鲁棒控制

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This paper investigates the robust dynamic output feedback non-fragile control (RDOFNFC) strategy for spacecraft attitude stabilization problem with nonlinear perturbations. The spacecraft attitude dynamics model takes the actuator saturation limits, external disturbances, controller perturbation and model parameter uncertainty into account. To make spacecraft attitude system satisfy 11,, performance and quadratic stability, with respect to the additive perturbation in initial state and multiplicative perturbation in decay phase, the corresponding RDOFNFC is designed respectively. Based on Lyapunov theory, the controller design is transformed into a multi-objective convex optimization problem based on linear matrix inequalities (LMIs). Simulation results based on the on-orbit servicing spacecraft show good performance under external disturbances, model parameter uncertainty and controller perturbation, which validates the effectiveness and feasibility of the proposed control method. (C) 2017 Elsevier Masson SAS. All rights reserved.
机译：本文研究了具有非线性摄动的航天器姿态稳定问题的鲁棒动态输出反馈非脆弱控制（RDOFNFC）策略。航天器姿态动力学模型考虑了执行器饱和极限，外部干扰，控制器扰动和模型参数不确定性。为了使航天器姿态系统满足11，性能和二次稳定性，关于初始状态的加性扰动和衰减阶段的乘性扰动，分别设计了相应的RDOFNFC。基于李雅普诺夫理论，将控制器设计转化为基于线性矩阵不等式（LMI）的多目标凸优化问题。基于在轨维修航天器的仿真结果表明，在外界干扰，模型参数不确定性和控制器扰动的情况下，该性能良好，验证了所提控制方法的有效性和可行性。 （C）2017 Elsevier Masson SAS。版权所有。

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