Synthesis of Nonlinear Model Matching Flight Control System for High Maneuver Vehicle

Up to the present various model matching systems have been proposed for linear system, but very little has been done for nonlinear system. Authors have already proposed several design methods of discrete time flight control system using nonlinear model matching. But those systems were constructed as the nonlinear control ones for the limited and small nonlinear maneuvers of aircraft from some steady flight condition. Practically most of aircraft are required to fly at several modes, for example zooming up, diving and turning movement. Therefore our nonlinear model matching flight control system should be extended to an available system for such mode. If this control system can be constructed, it can be also applied to the fundamental control system of various vehicles. In this paper, a design method of nonlinear model matching control system for high maneuver vehicle is proposed using a nonlinear equation of aircraft without giving the steady flight condition, in discrete time. This method is based on Hirschorn´s algorithm and facilitates easy determination of the control law using the relationship, between the output and the input, which is obtained by the time shift signals of the output. Also as a result, this method is the extension of the linear model matching control system proposed by Wolovich, in which the control law is obtained by left-multiplying the output by the interactor matrix. Yet it is assumed that all state variables can be measured, they are used in the control input signals.