| The main works of this thesis are research of lateral force control and guidance of interceptors, emphasized on the terminal phase when intercepting the tactical ballistic missiles, including the performance analysis of extra-atmospheric kinetic-kill vehicle piloted by trajectory-control and attitude-control systems, and combined control of aerodynamics with lateral jets in atmosphere. The main work and achievements are described as follows:(1) The analysis of the extra-atmospheric kinetic-kill vehicleAt first, the motion model and dynamics model of the kinetic-kill vehicle is constructed, and the thrust performance of trajectory-control system and attitude-control system are presented, then the algorithms of realizing the guidance law, the methods of trajectory and attitude control are studied. The simulation of the terminal guidance procedure is carried out, and the results verified the conclusion that the interceptor can hit the target directly. At last, the effect of flight path angle error on interception performance is analyzed in detail.(2) The study of combined control methods of an intercepting missile in atmosphere1. The parameters choice of intercepting missile. The whole scheme of the interceptor is chosen at first according to the characteristics of the mission, including the aerodynamic configuration and the control style. And then based on a surface-to-air missile that satisfies the requisition nearly, by means of reconstructing its geometry size, subsystems such as engine, the interceptor model used to continue the following studies is established. Then the trajectory-control jet or attitude-control jet is added to the interceptor based on the analysis of the relationship between the missile performance and the thrust and configuration of the side jet.2. On the basis of looking up a lot of referenced works, the phenomenon that lateral jet injected into the external air stream surrounding an intercepting missile is analyzed. The effects of jet interaction on forces and moments are described by interaction amplification factor, and the algorithm to calculate the interaction amplification factor is presented, then the motion model and the dynamics model of interceptor are established according to the previous analysis.3. The combined trajectory control system is designed. The direct force is acting on the pitch channel and the yaw channel, and the roll channel is stabilized by the fin surface deflection. By means of guidance command decomposed forwardly, the combined control system is divided into two parallel subsystems: the aerodynamics subsystem and the direct force subsystem. The aerodynamics subsystem is designed employing classical control methodology, including the inner loop which adopt angular rate feedback to stabilizing the attitude, and the outer loop which track the guidance command, and the proper emendation nets are designed for each loop. The simulation results show that the available load and performance of transit response have improved obviously.4. To solve the problems caused by the varieties of the missile dynamics with the difference of flight height, velocity and attitude angle in modeling the missile, in this thesis, the theory of variable structure model reference adaptive control is used to design a pitch channel autopilot based on a longitudinal missile model, the status equation using the measurable parameters of load and angular rate is established, and the methodology to choosing the reference model is discussed also, and the performance of the controller is analyzed by means of simulation.5. Aiming at the specific mission that intercept the warhead of tactical ballistic missile, the new issue for designing the guidance law is analyzed, and a new guidance method that fit for the mid-course is presented, based on the idea of predicting the intercept point. To design a feasible terminal guidance law, the shortcoming existing in the proportional navigation when intercepting the warhead is firstly...
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