Target Assignment And Cooperative Guidance Of Multiple Intercertors

Since the beginning of the 21st century,with the rapid development of anti-missile system and the rapid complexity of battlefield environment,this makes the battlefield survival rate of very low when a single missile is engaged in combat,and this method of warfare can no longer meet the needs of modern warfare,multi-interceptor cooperative combat can expand the attack effectiveness and improve the hit rate,which has shown great advantages.More and more scholars into the study of multi-interceptor missile coguidance.Based on the research background of multi-interceptor coordinated combat,this paper studies the problems of target distribution,collaborative guidance and interceptor attitude control in the process of coordinated combat.It is divided into the following main research contents:Firstly,the motion equation of the interceptor is derived,and then the attitude control model and relative motion equation of the interceptor are established,which provides a theoretical basis for the design of attitude control algorithms and cooperative guidance laws for subsequent interceptor missiles.Secondly,the calculation method of intercepting the success rate of intercepting target is proposed,the performance index function is designed on this basis,and the target distribution model in cooperative combat is established,and a target allocation algorithm based on genetic particle group is designed according to the defects of traditional optimization algorithms,and the simulation found that the algorithm has great advantages in solving high-dimensional target assignment problems.Then,a time angle co-ordination guidance law is designed,in the two-to-one scenario,four methods of calculation of residual attack time estimation are proposed,the four methods are analyzed with precision,and a specific time estimation method is selected,the sliding mode and optimal control theory are used to design time and angle constrained guidance laws,and two guidance law switching methods are adopted to form a hybrid constrained guidance law.Interception experiments are carried out for stationary and maneuvering targets.The experiment found that the guidance law satisfies the impact angle indicators on the premise that each interceptor hits the target at the same time.Finally,the attitude control algorithm of interceptor is designed by ADRC theory,the coordination state is estimated based on ESO,and base on the second-order consistency theory,design a three-dimensional time cooperative guidance law considering attitude control and state estimation.Because of the singular problem of the guidance law,different switching strategies are proposed.The characteristics of different control laws and switching strategies are analyzed,and six-degree-of-freedom cosimulation of guidance and control is designed,which proves the effectiveness of the design.