基于分块反步设计的飞行器姿态稳定鲁棒控制  

Robust Attitude Control of Aircraft Based on Partitioned Backstepping

作　　者：毕胜[1] 季海波[1] 

机构地区：[1]中国科学技术大学自动化系,合肥230027

出　　处：《宇航学报》2008年第6期1878-1882,共5页Journal of Astronautics

基　　金：国家自然科学基金(60674029);高等学校博士学科点专项科研基金(20050358044)

摘　　要：采用分块反步设计思想,结合输入状态稳定性理论,获得了一种具有鲁棒性能的飞行器姿态稳定控制方案。该方案可自然地处理姿态耦合问题,实现半全局姿态稳定控制,并对外部扰动具有鲁棒性,可直接应用在燃气动力的情况。对某空间飞行器的姿态控制系统进行了数值仿真,仿真结果验证了该方法的有效性。This paper proposes a robust nonlinear attitude control method for aircraft based on partitioned backstepping method and input-to-state stability theory, With this strategy the coupling of the model attitude can be dealt naturally, A stable attitude control is realized semi-globally and the scheme has a good robust property subjected to external disturbances. The control design can be applied directly to an aircraft with thrust arising from gas fuel. A numerical simulation of an attitude control system is performed and the simulation results show that the control method designed in this paper is effective.

关 键 词：分块反步设计法 输入状态稳定性 姿态控制 

分 类 号：V249.122[航空宇航科学与技术—飞行器设计]