Research On Analysis Method Of Integrated Estimation And Guidance System For Highly Maneuvering Target Interception

With the rapid development of aerospace and guidance technology,dealing with the threat of highly maneuvering targets has highlighted urgent application needs in the field of homeland air defense.Compared with traditional interception targets,such targets fly at a high speed during the reentry phase and often have maneuverability comparable to missiles.Successful interception requires a very small miss distance or even a direct collision.Due to the obvious decline of the missile’s overload advantage,the traditional method of independently designing the estimator and the guidance law based on the separation principle is difficult to ensure an ideal interception performance.The integrated estimation and guidance(IEG)strategy provides a new solution for the highly maneuvering target interception(HMTI).An independent mode decicion-maker is introduced to estimate the current motion mode of the target,and different estimator and guidance law combinations are selected according to different guidance stages and different maneuvering states of the target.The IEG strategy is effectively verified in the terminal guidance and interception problem of highly maneuvering targets.The three components of mode decision maker,estimator and guidance law interact to determine the interception performance of the IEG system.In this paper,oriented to the application requirements of HMTI,the system analysis method research is carried out under the IEG system frame,and the influence of the mode decider,estimator,and guidance law on the interception performance of the system is comprehensively discussed.The work of the paper is of important theoretical significance and reference value for the design and performance evaluation of the IEG system.Chapter 1 first introduces the research background of HMTI in combination with military application requirements,and gives the important significance of the research on the IEG system analysis method.Then,from the perspective of estimation and guidance,the main problems and challenges faced by HMTI are pointed out,which leads to the necessity of adopting IEG strategies.Then,from the perspective of system design,the research progress of estimator,guidance law and IEG system are introduced,respectively.Subsequently,the research progress of HMTI system analysis is introduced,especially the research work related to IEG system analysis.Finally,the main work and content arrangement of the full text are given.Chapter 2 starts from the design requirements of the estimator,and analyzes the influence of the mode decision delay on the state estimation accuracy,and establishes the analytical distribution model of the zero-effort miss(ZEM)estimation error.Firstly,the general motion model of terminal guidance for planar interception is given.Subsequently,by modeling the target’s lateral acceleration command as a jump-Markov process,and under the assumption that the mode decision-maker has a fixed time delay,the error model of ZEM under the condition of model mismatch in continuous/discrete time system is derived,respectively.Quantitative analysis of the impact of model decision delay on state estimation accuracy is conducted.Finally,according to different estimated performance constraints,the performance requirements of the mode decision-maker,seeker and target maneuver are discussed,respectively.The analytical model of the ZEM estimation error derived in this chapter can replace the Monte Carlo method to effectively guide the design of the state estimator,and lay the foundation for evaluating the probability distribution of the system miss distance.Chapter 3 comprehensively analyzes the influence of the mode decision-maker,estimator and guidance law on the system’s interception performance based on the ZEM estimation error model,and establishes an statistical distribution model of the miss distance.Firstly,considering the system without disturbance(i.e.,the lateral acceleration command of the evader is always zero)and the system with Bang-Bang disturbances,the recursive expression of the probability distribution of the miss distance in discrete-time system is solved.On this basis,considering the limit situation where the time sampling interval tends to infinitely small,the partial differential form of the miss distance in continuous time system is obtained.Finally,the accuracy of the model is verified through five different types of disturbances.The analytic distribution model of miss distance derived in this chapter can replace the Monte Carlo method to effectively improve the design efficiency of the IEG system,and can provide a theoretical tool for evaluating the interception performance.Chapter 4 starts from the design requirements of the mode decision-maker,and derives the maximum admissible mode decision delay(MAMDD)of the system under the given constraints of different estimation performance,which can provide a theoretical and methodological basis of the index design for the mode decision-maker in IEG systems.Firstly,the estimation error model of the state in continuous-time system under the multimode jumping situation is derived,and the upper bound of the mode decision delay and the lower bound of the mode sojourn time are obtained by constraining the state estimation error.Next,considering the characteristics of terminal guidance,a numerical calculation method of MAMDD is proposed by limiting the mean error of ZEM within the boundary of the capture zone.Finally,considering both the mean and variance of the ZEM estimation error,a numerical calculation method of MAMDD under the consistency constraint is obtained.The results show that,in order to put forward more stringent requirements for the mode decision-maker,the consistency constraint should be selected in the first stage of terminal guidance and the capture zone constraint should be selected in the latter stage.Chapter 5 analyzes the performance of the state estimator under different mode decision delay based on the design requirements of the estimator for the spiral maneuvering aircraft.Firstly,a general motion model is proposed through dynamic analysis,which provides a data input for the performance analysis of the state estimator.Then,by introducing two resonance components of the lift acceleration,the state estimator is designed,and the estimation performance of the extended Kalman filter and the unscented Kalman filter are verified,respectively.Finally,considering the mode switching cases,the mode decision-maker outputs the nominal value of the spiral frequency and then used as the mode input of the estimator,the performance of target state estimation under different mode decision delays is quantitatively analyzed.Research results can provide theoretical reference for the motion modeling of the spiral maneuvering target,the index design of the mode decision-maker and the performance analysis of the state estimator.Chapter 6 summarizes the main work and research results of the thesis,and points out the research direction.