Research On Control Law Design Method Of Supersonic Cruise Missile

Supersonic cruise missile has strong nonlinear coupling, it’s always hard to findmethods of controller design. The purpose of this thesis is to study attitude anglescontrollers for supersonic cruise missile in its climbing phase. The main contribution isas follows.First, the climbing phase trajectory of supersonic cruise missile is designed.According to the basic theory of flight mechanics, the three loops coupled nonlinearmathematic model of the missile is built, and then transformed to a linear model withthe hypothesis of light-disturbed. In addition, the mathematic model is analyzedaccording to the coupling character.A method using dynamic inversion and variable structure control with sliding-modeis proposed to control the missile base on the nonlinear mathematic model. Thenonlinear model is decoupled into three SISO systems by means of dynamic inversion.Then variable structure controller is designed for each loop. Following, a study ofmathematical simulation is given to prove that the controller has good dynamicperformance and robust.The other method of model-reference variable structure control with sliding-modeis designed to control the missile base on the linear mathematic model. A study ofmathematical simulation is also given to prove that the controller has good dynamicperformance and robust.In the condition of ideal and disturbance, the numerical simulations are used toverify the high performance of the two kinds of controllers and compare the two designmethods. The simulations show that the theory study of this thesis is effective andcorrect.The two methods of the attitude angles controllers design in this thesis base on thecoupling character of supersonic cruise missile. It lays some foundation of using newcontrol methods for the practical missile engineering.