Guidance And Control For Missile With Aerodynamic And Thrust

With the air-attack weapon becoming more and more high speed and highmaneuverability, it is urgent to improve the agility and accuracy of interceptor.Due to lack of aerodynamic quality in high attitude situation, controller of missilehas difficult to respond the guidance commond quickly and precisely. Thereforeresearchers turn to lateral thruster assisting aerodynamic for advanced controlperformance. According to the characteristics of missile with divert thrusters, thisdissertation focus on the guidance and control problem of endo-atmospheric missilewith blended control.First, configuration of lateral thrusters is confirmed, and the imfluences to missilecontrol brought with that are discussed. Considering direct forces, the kinematic anddynamic equations of missile is established, and in the meantime three degreemissile-target relative kinematic equation is given. Then above established modelsare simplified in some admissible assumptions. These results form the foundationfor later analysis and design.Second, basic design method of auto disturbace rejection controller (ADRC) isintroduced. Attitude control strategy is given according to the response speed ofstate, and control parameters tunning process is summarized briefly. Then controllerperformance designed is entirely analyzied by means of simulation.Third, through introducing a kind of ADRC guidance law, a target accelerationestimation method by taking advantage of extend state observer is extracted.Moreover, miss distance computation method considering target maneuverabiliywith constant acceleration is discussed. Then a kind of reducing predictive missdistance guidance strategy for blended system is formed combined with lateralengines ignition moment and ignition logic.At last, a simulation platform is established for a certain endo-atmosphereinterceptor. First of all, the influence of misalignment and lateral jet interactions isdiscussed. The effects brought with thruster ignition are shown through simulation.Then by six degree of freedom simulation, the validity of blended system controlstrategy and guidance strategy proposed above is proved. Finaly, the effect ofignition times and moment, mesurement error and noise in relative distance to hitaccuracy is analyzied compeletly by simulating.