Research On Midcourse Penetration And Field-of-View Constraint Precision Guidance Method For Air-to-Air Missile

Since the first application in the real war in 1940 s,after decades of development,air-to-air missile has become an important weapon for fighter to seize the air production right and war initiative.With the development of high-tech,the performance of air-to-air missile target aircraft is also improving,such as supersonic characteristics and high maneuverability,which brings challenges to its combat capability.In order to achieve the precise strike of high-performance target aircraft and effective penetration of intercepting weapons,air-to-air missile should have the matching precision strike ability and maneuvering penetration capability.The above requirements are higher requirements for the guidance technology of air-to-air missile.This thesis takes the penetration and field of view constraint precise guidance of air to air missile as the research object,studies the identification of the guidance law coefficient of interceptor,the design of the optimal guidance law of the middle penetration based on the identification parameters,the guidance information extraction under the condition of the active/semi-active radar seeker measurement noise,and the fixed time convergence angle constraint guidance law under the three-dimensional field constraints.The main research contents are as follows:The air-to-air missile faces the threat of anti air-to-air missile weapon(AAAMW)launched by the enemy.The traditional one side optimal penetration method only adopts linear interception law for AAAMW,and the penetration performance is poor when AAAMW adopts nonlinear interception law such as angle constrained guidance law.In view of the threat of air-to-air missile to the enemy interceptor system,the optimal maneuver penetration guidance law based on the set identification of extended interceptor law is studied.Firstly,by analyzing the intercepting mode of enemy,the angle constraint guidance law is introduced on the basis of traditional linear interception law,which forms the extended guidance model set;Then,the identification model of guidance law is established,and the guidance law is identified by interactive multi model adaptive filtering method.The method can estimate the form of guidance law and the parameters of guidance law.At the same time,the optimal one side control guidance law for the extended guidance law set is studied.The guidance law set of interceptor is represented in a unified form,and the relationship of missile and interceptor is substituted to obtain the single side optimal penetration model of missile.On this basis,the single side optimal guidance law of missile penetration is designed based on the optimal control theory.The simulation results show that the missile can identify the guidance law of intercepting weapon accurately and realize penetration.The effectiveness of the proposed guidance law identification and optimal penetration method is verified.Aiming at the guidance information measurement of air-to-air missile using active radar seeker,the acceleration estimation of maneuvering target based on improved multi model filtering is studied.Firstly,according to the flight characteristics of fighter target,the maneuver model set is modeled;In view of the large amount of computation of the traditional interactive multi model algorithm,a filtering period switching mechanism is proposed to improve the multi model filtering.The simulation analysis shows that the improved algorithm can reduce the computational burden on the basis of ensuring the estimation accuracy.Then,aiming at the situation that the passive infrared seeker can only provide angle measurement information when the active radar seeker is jammed,the inertial line of sight angle reconstruction algorithm and line of sight angular velocity estimation model are given.Considering the strong nonlinearity of the high-dimensional state equation and the non-Gaussian characteristics of the measurement noise,the Cauchy measurement update with stronger robustness is combined with the fifth-degree cubature Kalman filter with high numerical accuracy.The Cauchy higher-degree cubature Kalman filter is proposed to estimate the LOS rate.The simulation results verify the higher accuracy of the filtering algorithm under non-Gaussian noise.In order to maximize the damage effect of air-to-air missile,the terminal attack angle will be constrained.However,the curved trajectory shape is very easy to cause the target to exceed the field of view of the seeker,which affects the guidance accuracy.Considering the field of view angle and terminal angle constraints in the terminal guidance process,a fixed time convergent sliding mode guidance law is proposed for the high-speed maneuvering airplane interception.The method transforms the terminal guidance problem into the stability problem of the terminal guidance system.A novel time-varying sliding variable and barrier Lyapunov function are constructed.The ability of the constraint to the angle of view in the approach and sliding surface and fixed time convergence of the guidance law and are proved.Considering the influence of the lateral field of view angle on the available range of the longitudinal field of view angle in the end guidance process,a fixed-time convergence lateral guidance law is designed.The fast convergence of the initial large lateral field of view is realized;Thus,under the constraint of three-dimensional total field of view angle,the influence of lateral field of view angle on the available range of the initial longitudinal field of view angle is reduced,and the guidance pressure of the rear section is further reduced.In addition,by observing and compensating the target velocity components in the normal velocity and lateral velocity,the available range of the seeker field of view is increased,the overload capability of the aircraft can be fully exerted and the interception accuracy can be improved.