Terminal Guidance Simulation Of The Interception Of Boost Phase Missile

The problem of missile interception is one of the key research tasks in the present national defense system. The boost phase interception has some advantages such as detection convenience, war resources thrift, etc. And it is generally considered as the most effective stage to intercept. However, due to the big acceleration of the target and the short rise time during the boost phase, the technique of interception has still been studied under the technology pressure at present. This paper is based on the interception of boost phase GBI with a three-stage booster rocket. The passive tracking filter against high maneuvering target which is combined with the terminal guidance law, can give precise guidance effect.The acceleration of the booster-stage aircraft is large so it will consume more overload to intercept. In this paper, the adaptive extended Kalman filtering is applied to the passive detection of target acceleration estimation. And sliding mode variable structure guidance is applied to keep line-of-sight rate at zero. At the same time, the ballistic simulation of the interception problem in the three-dimensional space is carried out, and the effect of target maneuver and rendezvous angle is studied.Firstly, the development of the current boost phase interception and the tracking method of the maneuvering target situation is introduced. The motion model of the missile and target is established. Then we analyse the passive measurement condition with angular information known only. By comparing of several different target maneuvering model, we select singer model to describe the maneuvering target behavior and deduce the observation equation. The new guidance filter is derived based on the extended Kalman filter.Secondly, the relative motion relationship is analyzed in the longitudinal and lateral planes. The acceleration expression of the interceptor is obtained by applying the sliding mode variable structure guidance theory. To keep the line-of-sight rate stable near zero, the basic premise of high precision guidance can be ensured. Then we analyze the influence of the target’s maneuverability to required overload from two aspects which consist of maneuvering acceleration and crossing angle.Finally, the terminal guidance method above is used in boost phase interception instances. We analyze the initial conditions and the target motion parameters.And the engine thrust control method is elaborated. Subsequently, three situations with different initial velocity intersection angle are given. The effect of terminal guidance interception is validated in some guidance parameters such as fuel consumption, intercept time and required overload.