基于滑模控制的高超声速飞行器的轨迹控制  

Trajectory control of hypersonic flight vehicle based on sliding mode control

作　　者：薛丽[1] 管萍[1] 刘小河[1] 

机构地区：[1]北京信息科技大学自动化学院,北京100192

出　　处：《北京信息科技大学学报（自然科学版）》2011年第6期52-56,共5页Journal of Beijing Information Science and Technology University

基　　金：国家自然科学基金资助项目(51077004);北京市自然科学基金资助项目(4082010);教育部科技重点资助项目(207003);北京市教委科技项目(KM200611232007)

摘　　要：针对高度非线性、多变量、强耦合的高超声速飞行器的纵向模型,设计了飞行控制系统。首先对其进行输入/输出线性化,然后,选择2个解耦的滑动面,以改进的符号函数作为到达条件,设计了一种多输入多输出滑模变结构控制器。分别研究了飞行器对速度和高度阶跃指令下的响应,对标称模型和含有大范围时变参数模型进行了仿真研究。仿真结果表明该方法在存在参数不确定性的条件下,具有较强的鲁棒性能,能够满足系统的性能要求。Considering nonlinear,multivariable and strong coupled longitudinal mode of hypersonic aircraft,the plant flight control system is designed.First,the hypersonic vehicle mode is transformed into an affine system through input-output feedback linearization.Then,A multi-input/multi-output sliding mode controller is designed by selecting two decoupled sliding surfaces and the improved sign function is used as the reaching condition.The response of the vehicle under speed and high step instruction is studied.The comparison between the nominal model and the model with time varying parameters over large ranges is made.The simulation results show that the method has strong robustness and can meet the system performance requirements under the condition of uncertain parameters.

关 键 词：高超声速飞行器 输入输出线性化 滑模控制 鲁棒性 

分 类 号：V249.122.1[航空宇航科学与技术—飞行器设计]