航天器姿态指向跟踪的一种自适应滑模控制方法  

Adaptive Sliding-Mode Control for Spacecraft Attitude Pointing and Tracking System

作　　者：王冬霞[1] 石恒[1] 贾英宏[1] 周付根[1] 

机构地区：[1]北京航空航天大学,北京100191

出　　处：《空间控制技术与应用》2010年第6期22-26,共5页Aerospace Control and Application

摘　　要：航天器姿态指向跟踪(APT)技术是近年来引起深入研究的关键技术之一,设计一种自适应滑模控制律,通过设计自适应律考虑有界干扰力矩和转动惯量不确定因素的影响,同时使用滑模控制设计方法保证控制算法的鲁棒性,用双曲正切函数代替符号函数来克服滑模控制中存在的抖振问题,实现受控航天器的某个指向(相机或天线)保持对运动目标的跟踪.控制方案采用修正罗德里格斯参数(MRP)描述航天器姿态,用喷气推力器作为航天器的姿态执行机构.仿真结果显示了控制律的有效性.Spacecraft attitude pointing and tracking（APT） is one of key techniques to be lucubrated recently.This article is aimed to design a kind of adaptive sliding mode control law.Considering effects of some uncertain factors such as bounded disturbing torque and rotational inertia,the adaptive law scheme is designed.At the same time,a sliding mode control method is used to guarantee the robustness of control algorithm and it uses hyperbolic tangent function,instead of sign function,to avoid the buffet existed in sliding mode control,thus keeping a specific poiniting of controlled spacecraft tracking some moving object.In the control method,the modified Rodrigues parameter（MRP） is used to describe spacecraft attitude,and a jet thruster as the actuator.Simulation result shows the effectiveness of this control law.

关 键 词：姿态指向跟踪 自适应滑模控制 修正罗德里格斯参数 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]