Agile Target Maneuver Modeling And Air To Air Missile Guidance Law Design

The fifth generation of fighters and new generation of drones have been equipped,which bring new challenge to air-to-air missiles by emphasizing on high maneuverability and stealth.This thesis starts with the characteristics of air combat targets in the new situation,works on typical maneuvers of target evading missiles and guidance problems in noisy environments are conducted.Firstly,establishing the chase model of missile and target in three dimensions,investigate the typical maneuvers performed by targets when evading the missile.The kinematics models are established,which constitute the library of target maneuver model.Then,this article has carried on the statistics and the analysis to the library of target maneuver model,three of the most common functions are identified as fitting functions,the fitting order is optimized.The sampler,identification process and predictor are designed according to the target maneuver characteristics,which constitute the Maneuver identification predictor.Thirdly,studied the actual performance of the target maneuver.Using the public data,a target dynamic model was established and maneuvers in the maneuver model library were performed,the original kinematics model is replaced by dynamic model.According to the simulation result,the function library in the maneuvering identification predictor is expanded and the prediction accuracy is improved.Afterwards,the missile guidance problem under high noise is explored,the influence of noise on the miss distance is analyzed by simulation.For target information with measurement noise,combined with the special requirements of air combat,an adaptive Kalman filter is designed to reduce the noise.The simulation results show that the target information which is denoised by the filter can meet the needs of maneuver identification.Finally,aiming at the poor observation problems that caused by the complex electromagnetic environment,a more study of missile guidance loops is conducted.In the case that distance information cannot be obtained,and only the angular velocity of the sight line can be used,a modified proportional guidance law is designed.Sufficient guidance information can be obtained by the line-of-sight angular velocity.