Research On Target Assignment And Guidance Law For Cooperative Engagement Of Multi-missile

With the rapid development of missile and antimissile technology,the traditional single missile is getting worse and worse as a weapon against the target,and it can not meet the requirements of modern information warfare.How to improve the effectiveness of cooperative engagement of multi-missile as the main goal,to break the previous situation that each missile fight independently,multi-missile communicate with each other,information sharing,integrated operations,to further improve the probability of target damage,help to further improve the missile combat capability,to make it more adapt to the complex demands of modern warfare.First of all,the mathematical model of relative motion between missile and target and some related theoretical foundations are given,a nd then some simplifications and analyses are made.Then,some basic theories of sliding mode are briefly introduced.In view of its superior control performance and extensive application of various control systems,the sliding mode guidance law is studied in this thesis.Secondly,the target assignment problem of multi-missile cooperative operations is studied in detail.Based on different research backgrounds,two different target assignment strategies are proposed.First in air-to-air combat,in-depth analysis and research,and then a hierarchical evaluation system of threat index is established,which uses AHP to further quantify and analysis of each threat.Based on the basis of the evaluation results,a threat index model is proposed,and on this basis,a target assignment strategy is put forward,which can distribute air combat objects more quickly and rationally.Aiming at the problem of multi-missile cooperative against multiple targets,the distribution matrix of missile-target is taken as the optimization variable,and the maximum value of damage probability is taken as the objective function.An optimization model is proposed,and the genetic algorithm is further improved and optimized to get a good assignment scheme.Then,a mathematical model of multi-missile cooperative guidance is established,and it is decomposed into two subsystems along the line of sight,then the acceleration commands are designed respectively for two subsystems.Aiming at the subsystem of line of sight,the control command is proposed based on the consistency theory,and the requirement of cooperation is achieved.According to the normal line of sight to the subsystem,a non-homogeneous disturbance observer is proposed to estimate the outside disturbance.The proposed sliding mode guidance law with finite time convergence,Then,the cooperative guidance law is obtained by combining the acceleration commands of two subsystems,and further simulations are carried out.Finally,a time-varying NFTSM is proposed,and a sliding mode guidance law with finite time convergence is designed.In order to improve the control effect,the external disturbances existing in the guidance subsystem are analyzed and studied deeply.In view of the known upper bound of external interference,a coop erative guidance law based on super-twisting is designed by using super-twisting algorithm to estimate and track disturbances.In view of the existence of unknown upper bound of external disturbances,a hyperbolic tangent adaptive algorithm is used to estimate the disturbance.Another adaptive sliding mode guidance law is designed.Through theoretical and simulation verification,the proposed three guidance laws can estimate and track the external disturbances well,and can accomplish the task of cooperative guidance perfectly.