Research On Tracking And Guidance Algorithms Of Terminal High-altitude Missile Target

The ballistic missile system undertake the significant task of homeland strategic defense. The technique of missile tracking and guiding became a hot research issue for it is the critical technique in the mission of ballistic missile target defense in recent years. In order to meet the impending requirement of stabilized tracking and accurate guiding ballistic missile,this paper discuss the ways and algorithm of filter tracking, data correlation and guidance on terminal high-altitude ballistic missile, then stimulating and verified the algorithm. The ground work is as follows.First, using the method of Runge-Kutta integration, the stress situation of ballistic missile within and without atmosphere under the east-north-up coordinate system were stimulating and modeling respectively.At the aspect of missile tracking, according to the different cha racteristic of the two phases’ stress situation, the state and measuration’s equation has been built on the basis of EKF filter algorithm. A target tracking algorithm based on singer model was adopt to analysis the target which only affect by gravity outsider the atmosphere, and a target tracking algorithm based in the model of ballistic missile was used to solve the problem of mismatching between the maneuvering model on target tracking algorithm and the actual movement of the reentry objective. In order to solve the most co mplex problem--the tracking of multiple target, The Joint Probabilistic Data Association algorithm was adopted to simulate and verify the target outside the atmosphere after a full analysis of the common algorithm, which cannot filter the light and heavy bait through atmosphere.At the aspect of missile guidance, a brief introduction about the guidance system’s concept, function and procedure was described. Analysis about the common methods of missile guidance’s advantages and disadvantages was made. The proportional navigation guidance algorithm was deduced elaborately. According to the different proportionality coefficient, the result of missile filtering date ’s simulation was given by using the generalized least square method to smoothing the flight path.