非线性逆在ASTOVL控制系统中的应用

研究了先进短距起飞垂直着陆飞机（ASTOVL）的飞行／推进控制系统的控制律，基于解和掌握气动舵面和推力矢量舵面控制下的飞机数学模型，应用非线性动态逆理论，为ASTOVL飞机从巡航到悬停阶段的飞行，设计了推力矢量控制器和俯仰控制器，以合理地分配飞机上的力和力矩，使得俯仰姿态速度和法向速度的控制在推进系统性能包括线范围内是近似线性和解耦的，最后以ASTOVL飞机悬停阶段的数字仿真曲线为例，证明了所设计的两个控制器是可行的，基本上达到了设计要求。

Application of Non-Linear Inversion for ASTOVL Control System

The control law of flight/propulsion control system for advanced short takeoff and vertical landing(ASTOVL) is researched. During the flight from cruising to hovering, based on comprehending and grasping the fighter mathematical model under the control of aerodynamics and thrust vector, the theory of nonlinear dynamic inversion is successfully applied to design a thrust vector controller and a pitching controller. In this case, the force and the moment on the aircraft are reasonably distributed. And the three axis of pitching, longitudinal and normal are made to be linearized and uncoupled approximatively in the performance envelope of the propulsion system. Finally, the digital simulation results for ASTOVL during hovering show that the two controllers designed in the papers are very feasible and the designing aim is basically achieved.