Researh On Integrated Spiral Maneuver,Guidance And Control Of Reentry Warhead

With the requirement of modern warfare,precision guidance is leading a more and more significant role for ballistic missile than ever before.Meanwhile,in order to effectively contain the threat of ballistic missiles,anti-missile technology is also making continuous progress,posing a serious threat to the survivability of ballistic missiles.Therefore,for the warhead in the reentry phase,it is faced with the dual task of precision guidance and maneuvering penetration.Generally speaking,however,terminal precision guidance and it's maneuvering penentration a contradiction.So a new method named the design of integrated terminal spiral maneuver,guidance and control is poprosed in this paper,for the purpose of makinga coordinated design between maneuvering and guidance.Firstly,the coordinate systems are defined and their transform relationships are also given in order to describe the motion of the reentry warhead.On the basis of some reasonable assumptions,the space trajectory equation of the reentry stage,the attitude dynamics equation based on BTT control and the target kinematics equation are derived,which lays the foundation for the following research.In the next thesis,the integrate spiral maneuver and guidance is studied,the detailed method is given to solve the contradictory between maneuvering and guidance.Through the analysis of the geometric relationship between the reentry missile and target,the three-dimensional coupling dynamic equations of line of sight are deduced,based on which the three-dimensional sliding mode guidance law is also designed.Then,the control siganal of space spiral maneuver trajectory is studied,whice is consistent with the slide mode guidance law in forms.By studying the contribution to the integrated maneuvering guidance law of above signals espectively,a regulating coefficient was introduced in the integrated guidance law to weaken the overlimit to spiral maneuver ability from the slide mode guidance law.Besides,the stability of the integrated guidance law is proved by Lyapunov method.The simulation results show that the integrated guidance law can achieve the dual requirements of precision guidance and penetration for both static and moving targets,and the miss distance is not sensitive to maneuvering parameters.In the final thesis,the integrated spiral maneuvering,guidance and conrol is further studied,and for the purpose of solving the coordinated design of guidance and control system under the condition of large-scale spiral maneuvering in space.According to the integrated guidance law,the spiral maneuvering control command is given,the dynamic model of the integrated system is established,including the line of sight dynamics equations and the attitude dynamics equations.Then,the controller based on dynamic surface inversion control method is designed and the global stability of the controller is proved.The simulation results show that the designed controller has good dynamic characteristics and meets the dual needs of precision guidance control and penetration.