Study On Terminal Guidance And Control For Exo-atmosphere Kill Vehicle With Direct Force

This article mainly studies the Guidance Control of the latter end of exo-atmosphere kill vehicle (EKV). When EKV intercepts ballistic missile in exo-atmosphere, it needs a rapid response to the orbit maneuver of the target and finally kill the target using the kinetic energy of the collision. This entails a high requirement for the design of the Guidance Law and the control of the posture. In addition, while EKV intercepting of the latter end, the attitude control thrust is provided by the solid rocket motors. When designing the posture control systems, one should fully consider the impact brought by this thrust. Based on the properties of the interceptors outside the atmosphere, this article carries out the following work in the light of the above problems:First, this article builds up the six-degree-of-freedom simulation and analysis model outside the atmosphere and establishes the EKV orbital control engine model and posture control engine model.Secondly, this article studies the application of the sliding mode control theory to the design of the Guidance Law of the latter end of the kinetic energy interceptor. Based on the previous work, in order to solve the buffeting of the line of sight rate brought by the conventional Sliding Mode Guidance Law, this article introduces the Fuzzy Neural Network System to optimize the parameters of the variable structure terms of the Sliding Mode Guidance Law to weaken the buffeting. In order to avoid the low speed of the Online Learning of the Neural network system, this article uses a large number of prior data to train the Fuzzy Neural Network System offline so that the Fuzzy Neural Network System can obtain the parameters of the variable structure terms while Online Learning.Thirdly, taking into account the properties of Three-channel strong coupling and nonlinearity while controlling the posture of EKV, this article designs the EKV posture controller based on the Sliding mode control theory. In order to weaken the impact of buffeting and decrease the energy consumption of posture control engine, this article designs the intelligent control rules of the Sliding Mode Posture Controller. Also, this article chooses different control moment under different control errors and tries to weaken the buffeting as far as possible, as long as the control accuracy is guaranteed. Meanwhile, this article designs the Ignition method of compensation based on the unique executing agency, i.e. Group of bees pulse rocket engine, of the posture control of EKV. Simulation reveals that, the combination of Intelligent Sliding Mode Posture Controller and Ignition method of compensation can fulfill the posture control of the Kinetic energy interceptor terminal guidance.Finally, this article introduces the impact of centroid drift and thrust misalignment to the terminal Control of Kinetic Energy Interceptor into the design of the six-degree-of-freedom simulation model. Taking into account the Coupled attitude and orbit control of the Kinetic energy interceptor, this article carries out the simulated shooting test of the target under different Mobile forms and analyzes the impact of different forms of mobility to the miss distance. Simulation reveals that the combination of latter end of the guidance law, the posture controller and the algorithm for the attitude control engine ignition system can meet the demand of the Kinetic Energy Interceptor.