基于自适应滑模方法的航天器位置与姿态控制  

Position and attitude control of a spacecraft based on adaptive sliding mode approach

作　　者：宋斌[1] 马广富[1] 李传江[1] 

机构地区：[1]哈尔滨工业大学航天学院

出　　处：《哈尔滨工业大学学报》2008年第9期1353-1357,1362,共6页Journal of Harbin Institute of Technology

基　　金：国家自然科学基金资助项目(60674101);高等学校博士学科点专项科研基金资助项目(20050213010)

摘　　要：为了解决存在参数不确定和外干扰的航天器位置与姿态控制问题,提出一种自适应滑模控制方法.该方法用于控制航天器的位置和姿态,确保航天器执行位置与大角度机动,完成捕获和移除大空间目标的任务.提出的控制算法无需不确定的界,比传统的滑模方法容易实现.Lapunov分析表明,设计的控制器保证了位置与姿态的渐近跟踪.最后,将该方法用于航天器的位置与姿态控制,仿真结果验证了方法的有效性.To solve the problem of position and attitude control of a spacecraft in the presence of parametric uncertainties and external disturbances, an adaptive sliding mode control approach is presented. The proposed approach is employed to control the position and attitude of the spacecraft in order to capture and remove large space targets by performing position and large angle maneuvers. The proposed control algorithm eliminates the requirement of uncertainty bound and is easier to implement than the traditional sliding mode control approach. The proposed controller ensures the asymptotic position and attitude tracking through Lyapunov analysis. Simulation results are presented to demonstrate the effectiveness of the proposed design method.

关 键 词：位置控制 姿态控制 自适应滑模控制 航天器 机动 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]