Research On Guidance Problem Of Head Pursuit Air-to-Air Missile

With the advent of hypersonic vehicle in near space, there is a new challenge to theavailable missile defense system. In order to cope with this threat, it is necessary todevelop a new kind of defense system.This paper focuses on the guidance problem of head pursuit on the background ofinterception to hypersonic vehicles. The main content includes the handover conditionsof midcourse and terminal guidance, the optimal midcourse guidance, the correctionstrategy of command and the maneuvering target tracking.Firstly, the dynamical model of missile and model of missile-target relative motionare established, which is necessary for later work.Secondly, the handover conditions of midcourse are analyzed. Then the captureregion for head pursuit with the Proportional Navigation is deduced and the effect ofinitial detection error on handover of midcourse and terminal guidance is discussed.Thirdly, the optimal midcourse guidance is designed. The constraints of midcourseare provided and the mathematical description of the midcourse guidance is derived.Then the optimal control problem is solved by Gauss Pseudospectral Method. Thecorrection strategy of command based on carrier aircraft detection is given.Finally, the maneuvering target tracking is researched using the Extended KalmanFiltering (EKF). The tracking model is founded based on the current statics model.Following that, the EKF is introduced and then the maneuver of the target is estimatedby the EKF.