The Study Of Performance Analysis And Evaluation For Homing Terminal Guidance System

In the past few years, the missile plays an increasingly important role in the precision-guided weapons. The performance analysis and evaluation of the terminal guidance system(TGS) have been therefore taken seriously, which can support evidence to improve the accuracy of the TGS and make the missiles to adapt future complex environment. Conventional performance analysis and evaluation methods, however, maintain lots of demerits, such as the high research and development costs, the long development period, and the limited evaluation index, due to the dependence of the analysis and methods on the data of the flying trial and the simulation. Therefore, this dissertation is subsequently focused on the dynamic performance analysis, the robust performance analysis and miss distance of TGS:Based on the analysis of the particularities and the characteristics of the TGS, the TGS is mathematically described with the consideration of the mechanism of the TGS, which will lay the foundation for the further dynamic performance analysis, the robust performance analysis, the miss distance analysis and the performance evaluation.According to the complicated nonlinear characteristic of the system, a multi model decomposition method based on the gap metric nonlinearity measure is proposed to solve the dynamic performance analysis. Initially, the methods of gap metric nonlinearity measure and the multi model decomposition are proposed. The nonlinearity measure of TGS is analyzed via gap metric. Then the model of the TGS is decomposed to be mathematically described as a linear model set. Finally, the indicators and computational methods of dynamic performance are proposed based on the linear model set.According to the parameter uncertainties characteristic and the exogenous disturbance of the TGS, a new robust performance analysis frame is presented. The uncertainty model is established by analyzing the uncertainty of TGS. Based on these, the robust performance is analyzed and the robust stability conditions are derived via the the theory of absolutely stable with a finite domain. For the uncertainties of flight control system and estimation system, the analysis of the robust performance of TGS is investigated via the finite-time 2H norm.The analysis of the miss distance of the TGS is investigated is this work. The advanced adjoint model of TGS is established via the adoint method, which applies to the guidance law with a correction term. The miss distance closed-form expression of TGS is derived via advanced adjoint model. The influence of the system parameters, the target maneuver and the seeker noise on the root-mean miss distance is mathematically analyzed via the closed-form expression and the advanced adjoint model.Finally, the performance evaluation of TGS is studied in this dissertation. Initially, the problem descriptions for miss distance evaluation, the robust performance evaluation and the dynamic performance evaluation are proposed by analyzing the performance evaluation problem of TGS. The performance evaluation is studied for a certain TGS. The rationality of design parameters is analyzed by miss distance evaluation, the robust performance evaluation and the dynamic performance evaluation. The disadvantages of TGS are put forward, and suggestions are given on how to improve the performance of TGS.