基于TECS|H_□的无人机纵向着舰系统设计

Longitudinal carrier landing system design for UAV based on TECS|H_□

针对无人机纵向自动着舰,运用总能量控制系统建立无人机纵向自动着舰系统,根据纵向着舰导引系统速度为常数且具有抑制纵向风干扰的要求,设计基于线性矩阵不等式的H_□输出反馈控制器,通过对所设计的先锋无人机的纵向自动着舰导引系统仿真表明:通过升降舵和油门的协调控制,实现了速度和航迹的解耦控制,且该设计能满足着舰要求,能有效地抑制纵向风干扰的影响,具有良好的鲁棒性能.

Focused on longitudinal automatic carrier landing for unmanned aerial vehicle, total energy control technique was employed to develop longitudinal carrier landing system. In virtue of requirements of velocity equaled to constant and restrained longitudinal wind disturbance for longitudinal automatic carrier landing system, H∞ control theory, based on linear matrix inequalities （LMI） , was used to the design of the longitudinal carrier landing system. The resulting H∞ output feedback controller was presented. The automatic landing system for Pioneer Unmanned Aerial Vehicle （UAV） was simulated, and simulation result showed that decoupling control for velocity and flight path was achieved through coordinating elevator and throttle effects, and requirement of carrier landing and restrained longitudinal wind disturbance and excellent robustness was achieved by specifications of the design.