摘要
采用非线性前馈加线性反馈控制结构,利用伴随法生成最优上升轨迹,设计输出反馈控制律与输出跟踪控制律,证明其有条件渐近稳定;实现高超声速飞行器上升段的最优跟踪控制,将系统能观测和不能观测部分分离,降低了对传感测量系统的要求.仿真结果表明,该组合方法能够实现高超声速飞行器的最大能量爬升,同时能够实现对最优上升轨迹的稳定跟踪.
A control structure consisting of nonlinear feedforward and linear feedback is adopt and the optimal ascent trajectory is generated by the adjoint method.The output feedback control law and output tracking control law are designed,the conditional asymptotically stabilization is proved and optimal ascent tracking is established for the hypersonic flight vehicle.The system is separated by the observables so that the sensors are easier to be chosen.Simulation results demonstrate that the maximum energy climbing could be realized by the proposed method for the hypersonic flight vehicle and the optimal ascent trajectory could be asymptotically tracked.
出处
《哈尔滨工业大学学报》
EI
CAS
CSCD
北大核心
2011年第7期131-134,共4页
Journal of Harbin Institute of Technology
基金
武器设备部预研基金资助项目(9140A13010410HK03)
关键词
伴随方法
输出反馈
渐近稳定
高超声速
跟踪控制
adjoint method
output feedback
asymptotically stable
hypersonic
tracking control
