Research On Missile Guidance And Control System With Multiple Constraints

In recent years,performance of tactical missile has been improved with the increasing development of new technologies.Meanwhile,active defense capability of the target is getting stronger,which makes conventional attack fail to exert maximum damage to destroy the target.Consequently,higher demand for missile guidance and control system is proposed.Techniques in guidance and control system represents the important part to guarantee the implement of precision strike of modern weapons.In this paper,guidance and control problems with constraints are investigated,three control techniques,namely,optimal control,sliding mode control,and fuzzy control are used in the analysis of missile guidance and control system.Main results are as follows.First,nonlinear dynamic model of missile movement is established under basic assumptions and simplifications based on missile kinematic and dynamic equations.Second,guidance problem with impact angle constrains is analyzed.Guidance problem in 3-D space is decoupled into two separate plane,in which guidance law has been derived.State equations is derived with the linearization of simplified model,with which an optimal sliding mode guidance law has been derived using both optimal control theory and terminal sliding mode control technique.System Lag of an autopilot has been considered when designing the guidance law,and an optimal guidance algorithm is derived with the help of Schwartz's inequality.Then,problem of coordinated guidance is considered.In the background of Conventional laser beam rider coordinated guidance,real-end induced by disturbances is analyzed,and a disturbance judging model is constructed.Considering both impact time and angle constraints,a guidance law has been derived based on terminal sliding mode control method to meet the requirement of impact time and angle.Fuzzy switching rules are constituted on the basis of fuzzy control theory,and a 3-D guidance law has been deduced with double constraints simultaneously.Fourth,a 2-loop autopilot has been designed.Nonlinear control dynamics is linearized with some basic assumptions and simplifications.LQR,together with its extended forms,is investigated in the application of autopilot design.Finally,from the view of simulations of missile movement in six degrees of freedom,a software has been designed with the function of switching various control methods,which is convenient for users to operate.