Research Of Guidance And Control Method Of Guided Projectile

Accurate combat has become the basic mode of operation of modern warfare.Guided projectile,on the one hand,have inherited the characteristics of low cost and perfect launching platforms of conventional artillery shells,meanwhile they have the advantages of high precision missile with small damage incidental.Therefore,the study of guided projectile has always been the focus of military development in various countries.Guidance and control system design is very important for guided projectile.In this paper,aiming at a guided projectile,the paper studies some key technical problems in guidance and control.First of all,in order to meet the need of precise strike,a composite guidance system of mid-guidance + final guidance was designed for self-seeking guided projectiles.The midguidance track was used to track the standard trajectory and the final guidance section was guided by three-dimensional proportional guidance.On this basis,guided ballistic program trajectory characteristics analysis,projectile dynamic characteristics analysis and overload analysis,which laid the foundation for further guidance control system design.Secondly,the one-dimensional visual effect search rule is analyzed,and the position of the optical axis of any instantaneous guided missile seeker is deduced.Based on the onedimensional visual search rule,an instantaneous capture domain is established as an oval capture domain model.An analytical expression of the position and the long and short axes of the instantaneous capture domain is given.Based on this,Target capture criteria is deduced.Aiming at the ballistic trajectory scheme and projectile dynamic characteristics of guided projectile,the overall scheme of guidance and control system is designed.Carried out the classic two-loop overload autopilot design,given its design parameters of the analytical expression.With the analytic solution as the initial value,the design parameters of the overloaded autopilot are optimized by using genetic algorithm,and the influence of the weight of the optimization objective function on the optimization result is analyzed and discussed.In the meantime,the advanced guidance network design is made for the middle guidance segment,and the parameter solving method of the advanced correction network is given.Finally,on the basis of the above work,six-degree-of-freedom trajectory simulation of self-searching guided projectiles was carried out.Considering the target of four different movement characteristics,the ballistic characteristics of the guided projectile,the movement characteristics of missile projectile and the field of view of the seeker are obtained.The simulation results show that the designed guidance control system can effectively eliminate the trajectory deviation and improve the accuracy of hit.