Research On Terminal Guidance For High Maneuvering Target Intercepting

This dissertation studies for problems in high-speed maneuvering target interception during terminal guidance process. The main work includes mathematical models for the missile target relative motion establishing, target maneuvering acceleration estimation filter design, terminal guidance law considering overload response design and hypersonic aircraft interception integrated simulation.Firstly, the dissertation establishes mathematical models of missile-target relative motion relation, given the neccesary coordinates and their associated conversion relationship.Secondly, target maneuver estimation methodbased on a single model is studied. State equations are established conbining with missile-target relative motion equations using Singer model or the "current" statistical model as target maneuvering model, and with unscented Kalman filter(UKF) method, two target maneuver estimation filters are presented.Then, target maneuver estimation methodbased on interacting multiple model(IMM) algorithm is studied. Conbining Singer model and the "current" statistical model, filter based on IMM algorithm is presentd.And filters’ performance is verifyed through simulation.Then, terminal guidance law is designed based on active disturbance rejection control(ADRC) method. Inner control loop is designed for overload response characteristic which is modeled as a second order system, and the terminal guidance law also consider target maneuver compensation.Finally, three typical target maneuver modes including cross range maneuver, longitudinal skip maneuver and terminal dive maneuver summed from the actual near space hypersonic vehicle flight is persented, and effectiveness of designed filters and terminal guidance law is proved by simulation.