Missile Attitude Control System Based On Trajectory Linearization

This paper studies the maneuvering warhead for air rudder control what instead of thrustvector control.The offensive weapon having very high strategic. Especially,When we attackcarrier battle group who have Perfect defensive system, the reentry maneuvering warhead willattack from carrier battle group Above. Can be avoid it very good for the enemy’s defensesystem by high speed of flight,especially Advanced attitude control method. Finally,tocomplete the target task. Currently, only the United States and a few other countries possessthe technology. Our country is only the primary stage of the theoretical study. In order tomake China’s Marine rights has been consolidated, We must act as a deterrent against enemyaircraft carrier. Therefore, we must develop the related technology of reentry maneuverwarhead. In this article,we design of pitch channel controller what it’s mainly aims at theproblem when the warhead in the reentry it is difficult to control. I hope for our country in thiswarhead aspects of the theoretical research to make the contribution.This kind of warheads due to the need for two times successively through the atmosphereand it’s flight speed has been reached supersonic level. The coupling between the parametersof very strong and it’ll cause strong nonlinear variation. So choose the suitable nonlinearcontrol method is a priority. At present, the nonlinear control various ways, but control thiswith a strong nonlinear variation aircraft are difficult to do. In this paper by using the dynamicinverse method to design the corresponding controller, and on this basis the trajectorylinearization controller has been designed. Concrete work contents are as follows:First, determine the pitch channel mathematical model of reentry maneuver warhead.The warhead mathematical model we are through the flight environment and status similar tothat of the aerospace vehicle mathematical model through certain assumed conditions and toomit the engine thrust in a three coordinate axis of three components of forces eventually got.Through the single channel model reduction, Finally got the pitch channel of themathematical model in this paper.Second, we designed the dynamic inverse controller of the pitch channel. We Used thetime scale separation method to the design of attitude angle inverse system and angularvelocity inverse system. The simulation results show: Angle of attack can well track controlinstruction.Third, we designed the trajectory linearization controller of the pitch channel. We designthe trajectory linearization controller is based on the dynamic inverse controller. Thesimulation results show that this control method is effective. At the end of the article we conducted perturbation experiments. With the increasingperturbation numerical. The dynamic inverse controller Angle of attack of the response isunable to track. But the trajectory linearization controller for control performance is still good.This shows that The trajectory linearization controller is robust and very suitable for this kindof missile design requirements.