摘要
以空间应急飞行器姿态机动快速控制过程为研究对象,对姿态快速解耦控制问题进行研究。采用决策树理论对时间最优控制和倾斜开关曲线控制这两种控制策略进行综合,以控制时间作为代价函数,获得三通道时间最优控制策略。与其他方法相比,本控制策略控制时间大幅缩短,控制精度满足设计需求。另外对控制器不同控制周期下的控制效果进行仿真比较,对控制器控制周期选择具有指导意义。
The control process for the fast maneuvers of the responsive spacecraft was taken as the research object, and the rapid decoupling of the attitude control problem was investigated. A comprehensive control strategy which integrates time optimal control and tilt switch curve control was proposed based on the decision tree theory. Furthermore, the control time was taken as the cost function, the three-channel time optimal control strategy was obtained. Compared with other methods, the control time of the proposed strategy is reduced by nearly 10 seconds, and the control precision meets the design requirements. Additionally, control results were compared in case of different control cycles for the controller, and the instructional conclusions were provided for selecting and designing of the control cycle.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2012年第4期49-53,共5页
Journal of National University of Defense Technology
基金
国家863计划资助项目
关键词
姿态控制
时间最优控制
姿态解耦
决策树理论
attitude control
time optimization control
attitude coupling
decision tree theory
