摘要
针对高超声速飞行器模型的强非线性、快时变、强耦合和强不确定性,提出了基于动态逆和Terminal滑模控制的制导/姿控一体化设计方法。该方法将动态逆控制的非线性解耦能力与Terminal滑模控制的强鲁棒性有机结合,实现了模型的反馈线性化和多通道解耦,保证高超声速飞行器在存在参数不确定性和外界干扰的条件下实现稳定飞行。仿真结果表明该控制方法对高超声速飞行器是可行的。
Based on dynamic inversion and terminal sliding mode control method, a method of integrated design of the guidance and attitude control for hypersonic flight vehicle is proposed according to the feature that hypersonic vehicle model is highly nonlinear, strong coupling and great uncertainties. The nonlinear decoupling ability of dynamic inversion with the strong robustness of terminal sliding mode control is com- bined very well in this method. Thus, the nonlinear longitudinal dynamic model of hypersonic flight vehicle can be linearized completely from the Input^Output point of view by feedback linearization. The terminal sliding mode control system can ensure the longitudinal flight stability under the influence of uncertain parameters and outside interference. The simulation results show that the proposed control method is feasible for hypersonic flight vehicle.
出处
《航天控制》
CSCD
北大核心
2012年第5期9-14,20,共7页
Aerospace Control
基金
国家重点基础研究发展计划(973)
关键词
高超声速飞行器
纵向模型
动态逆控制
TERMINAL滑模
一体化设计
鲁棒性
Hypersonic flight vehicle
Longitudinal model
Dynamic inversion control
Terminal slidingmode control
Integrated design
Robustness
