Research On Guidance & Control Method Of Interceptor Missile With Aerodynamics And Lateral Thrust Blended

With the rapid development of missile technology, the interceptor missile as a kind of advanced antimissile weapons got more and more attention during the modern warfare. It was necessary for interceptor missile to enhance maneuverability, which to copewith the threat from tactical ballistic missile. It was a most effective solution to augment the maneuver of endo-atmosphre interceptor missile in antimissile system by using aerodynamics and lateral thrust blended and that is getting more regards. In this paper, the guidance and control problems of interceptor missile with aerodynamics and lateral thrust blended was researched.Firstly, the mathematical models of interceptor missile with aerodynamics and lateral thrust blended were constituted. It was definited that requisite reference frame and transform relation of reference frame, on which movement equations were presented based for interceptor missile with aerodynamics and lateral thrust blended. These equations established the groundwork for the successive research, which included the model of aerodynamical rudders, the model of pulse thrusters, the jet interaction effect of pulse thruster using jet interference factor.Secondly, the guidance method was presented for the interceptor missile with aerodynamics and lateral thrust blended. The interceptor missile-target relative geometry relation in three-dimensional space was constituted. A sliding mode guidance law was designed including the method to compute relative distance between interceptor missile with aerodynamics and lateral thrust blended and target and the method to count the coefficient of switching function and the method to amend of switching function in order to overcome the chattering of sliding mode guidance method. The simulation results proved the validity of this guidance method.Thirdly, the control method was presented for the interceptor missile with aerodynamics and lateral thrust blended. The blended control strategy just only distributed aerodynamics and lateral thrust with the terminal of guidance, not only made use of the fuction of aerodynamical rudders but also ensuured optimal of aerodynamical rudders and flap and pulse thrusts. Basing on the control model of interceptor missile with aerodynamics and lateral thrust blended, the dynamics inverse control method of interceptor missile with aerodynamics and lateral thrust blended was presented, anding an extended state observer to estimate unknown disturbance, which overcome the dynamics inverse method's defect on precise meth model. The simulation results proved the validity of this control method.Fourthly, the fire algorithm of pulse thrusters was presented for spinning interceptor missile with aerodynamics and lateral thrust blended. According to different fire principles, the new fire algorithms of pulse thrusters were presented, and which analyzed the advantage and defects of this fire algorithms.Considering the effect of spinning motion of interceptor missile with aerodynamics and lateral thrust blended to lateral thrust, the track error of fire command was compensated and the genetic operation of simple genetic algorithm was improved. Optimizetion of fine quantity of pulse thrusters used the improved genetic algorithm. And then searching online depended on optimize results ensure precise of lateral thrust of pulse thruster. For these bases, the opration progresses of fire algorithm of pulse thrusters were presented. The simulation results proved the validity of this fire algorithm.Finally, the guidance and control simulation platform was designed for the interceptor missile with aerodynamics and lateral thrust blended. Analyzed the requirement of guidance and control simulation platform and designed the framework of the guidance and control simulation platform and constituted the guidance and control simulation platform of interceptor missile with aerodynamics and lateral thrust blended. The guidance and control simulation test was realized through the platform for the interceptor missile with aerodynamics and lateral thrust blended. The simulation results demonstrate the feasibility and validity of guidance and control methods of interceptor missile with aerodynamics and lateral thrust blended.The research work provided an effective solution for guidance and control problems of interceptor missile with aerodynamics and lateral thrust blended, which estimated the academic base of further research.