Research On Guidance And Control Technologies Of Air-to-Ground Missiles

The guidance and control systems of TV-Command-Homing Air-to-Ground Missile (TVCHAGM), as well as the interrelated problems in combats and deployments, are thoroughly researched in this paper. Mainly, thereinafter several research subjects are involved:1. The model of each subsystem related to the TVCHAGM's guidance and control system is researched. The error rules of the strapdown INS are researched. Then the stable track model of the TV seeker is built, and a controller is designed to decouple the seeker's output from the missile's gesture angle. Afterwards, the man-in-loop model is built. At last, the effects of various optical factors on the operation distance of the TV seeker are researched.2. The robust autopilot of the TVCHAGM is designed by two kinds of control theory:(1) Based on online neural network, an adaptive dynamic inversion autopilot system of the TVCHAGM is designed. An online neural network is adopted to eliminate the inversion error, which originates from the perturbation of the model's parameters. Afterwards, considering the disadvantageous effects on the update process of the neural network's weights aroused by the unmodeled dynamics of the actuators, pseudo control hedging is introduced to improve the system's command following performance when the actuators'unmodeled dynamics exists.(2) A robust missile autopilot system is designed based on backstepping and sliding mode. Firstly, for a class of multi-input-multi-output uncertain nonlinear system with unmodelled dynamics and external disturbances, a robust controller based on backstepping and sliding mode control was designed. The unknown dynamics and external disturbances were estimated by a RBF neural network. Secondly, the scheme is applied to design the autopilot system of TVCHAGM. Considering the needs to overcome the disadvantageous effect of the actuator's position saturation and velocity saturation on the system's performances, the sign function is modified and fuzzy logic is introduced to modulate the slope of the slide surface in real time. Finally, its performance is compared to the neural network dynamic inversion autopilot system on condition of pneumatic parameters perturbation, external disturbances and actuator's delay. 3. According to the characteristics of the flight process of TVCHAGM, the guidance process is divide into two phases——midcourse guidance phase and terminal guidance phase, which are both researched as follows:(1) Midcourse guidance phase——The flight path angle commands are created in real time according to the way points loaded before flight. Then the gesture angle commands are created based inverse dynamics. Thereafter, the generalized error model is built. Finally, an integrated midcourse guidance and control system of the TVCHAGM is designed.(2) Terminal guidance phase——According to the facility specialty and the combat task of the TVCHAGM, and by adding a time variant biasing item, a modified proportion terminal guidance law is designed. It can endow the missile the ability of vertically hitting the target. Then the software and hardware needs and the applicability to the missile are researched. Moreover, it is compared with a proportion plus integration terminal guidance law actually having been applied to a certain kind of TVCHAGM. The simulations show its excellent performance.4. Based on finite state machine theory, the TVCHAGM attack process under electromagnetic jamming condition is analyzed. And the whole trajectory simulation system of the missile is designed. Then choosing typical targets and battlefield environments and adopting Monte-Carlo method, a great deal of simulation is made. By this way, the missile's guidance and control precision and combat effectiveness is researched.The effectiveness of robust autopilot system, guidance system and the related research work presented in this dissertation is verified by theoretical analyses and intensive simulations.