一种改进的自适应滑模控制及其在航天器姿态控制中的应用  

An improved adaptive sliding mode control for spacecraft attitude control

作　　者：丛炳龙[1] 刘向东[1] 陈振[1] 

机构地区：[1]北京理工大学自动化学院,复杂系统智能控制与决策重点实验室,北京100081

出　　处：《控制与决策》2012年第10期1471-1476,共6页Control and Decision

基　　金：国家自然科学基金项目(10872030);北京理工大学科技创新计划项目(CX0428)

摘　　要：针对刚体航天器的鲁棒姿态控制问题,提出一种改进的自适应滑模控制(ASMC)算法.该算法除了不需要事先知道扰动及系统参数不确定性的上界外,还有效地解决了现有ASMC设计中对切换增益的过度适应问题.该算法具有以下优点:1)自适应的切换增益更接近扰动及参数不确定性的上界,能够产生低抖振的控制信号;2)控制力矩更为平滑,适于工程应用.仿真结果验证了所提出算法的有效性.An improved adaptive sliding mode control（ASMC） strategy is presented to address the robust attitude control problem of uncertain rigid spacecraft. The proposed ASMC algorithm provides an effective solution for the over-adaptation problem in current ASMC design and removes the requirement of a prior knowledge of the upper bound of the model uncertainty as well. The advantages of the proposed method are twofold. Firstly, the resulting switching gain is much smaller and a lower-chattering control signal is generated. Second, the corresponding control torque is smoother, which is more suitable for engineering applications. Simulation results show the effectiveness of the proposed strategy.

关 键 词：自适应滑模 姿态控制 非线性 低抖振 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]