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A Higher-Order Sliding Mode Three-Axis Solar Pressure Satellite Attitude Control System

机译：高阶滑模三轴太阳压卫星姿态控制系统

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摘要

This paper presents the design of a higher-order sliding-mode control system for the three-axis attitude control of spacecraft using solar-radiation pressure in a finite time. The spacecraft, equipped with four solar plates, is assumed to be orbiting in an elliptic orbit. The nonlinear spacecraft model includes uncertain parameters and external-disturbance moments. The objective is to control the roll-, pitch-, and yaw-angle trajectories of the spacecraft along prescribed reference trajectories using the solar plates. A higher-order sliding-mode control system is designed which consists of (1) a nominal nonlinear finite-time-stabilizing control law designed based on the notion of geometric homogeneity, and (2) a discontinuous sliding-mode control law to attenuate the effect of uncertainties in the model. For the synthesis of this control system, the attitude-angle errors and their first two derivatives are used. It is shown that in the closed-loop system, the attitude error as well as its first and second derivatives converge to the origin in a finite time. Then a high-gain observer is designed to estimate the first and second derivatives of the attitude-tracking error for synthesis, using only attitude-angle measurement. The closed-loop system including the observer achieves a fast recovery of the performance of the state-feedback higher-order sliding-mode control system. Simulation results are presented which show precise attitude control of the satellite, despite uncertainties in the model, using state variable as well as output feedback. (C) 2015 American Society of Civil Engineers.
机译：本文提出了一种在有限时间内利用太阳辐射压力控制航天器三轴姿态的高阶滑模控制系统的设计。假定装有四个太阳能板的航天器在椭圆轨道上绕行。非线性航天器模型包括不确定参数和外部扰动力矩。目的是使用太阳能板沿规定的参考轨迹控制航天器的侧倾，俯仰和偏航角轨迹。设计了一种高阶滑模控制系统，该系统包括（1）基于几何均匀性概念设计的名义非线性有限时间稳定控制律，以及（2）削弱滑模控制律的不连续滑模控制律。模型中不确定性的影响。对于该控制系统的综合，使用了姿态角误差及其前两个导数。结果表明，在闭环系统中，姿态误差及其一阶和二阶导数在有限的时间内收敛到原点。然后设计一个高增益观测器，仅使用姿态角测量来估计姿态跟踪误差的一阶和二阶导数以进行合成。包括观察者在内的闭环系统实现了状态反馈高阶滑模控制系统性能的快速恢复。仿真结果表明，尽管模型存在不确定性，但仍使用状态变量和输出反馈显示了精确的卫星姿态控制。 （C）2015年美国土木工程师学会。

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  • 来源
    《Journal of aerospace engineering》 |2016年第1期|04015019.1-04015019.15|共15页
  • 作者

    Lee Keum W.; Singh Sahjendra N.;

  • 作者单位

    Catholic Kwandong Univ, Div Elect Informat & Commun, Gangwon 210701, South Korea;

    Univ Nevada, Dept Elect & Comp Engn, Las Vegas, NV 89154 USA;

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