Research On Design And Simulation Of Guidance Law For Anti Near-space Vehicle Missile

With the rapid development of near space hypersonic vehicle, the future war will be the sea air and space integration of war. Near space hypersonic vehicle with military strategy background is a huge challenge to the existing air defense anti-missile interceptor. Based on this background, this paper studies the guidance law design problem of air defense anti-missile interceptor, including the following three aspects:Firstly, aiming at the target of near space hypersonic reentry vehicle, a compound guidance law of interceptor is designed, and the interception of the high altitude and long distance is realized. The compound guidance law is consisting of three stages as follows: the high throwing program angle is designed in the beginning stage, the predictive proportional middle guidance law is designed in the middle stage, and the sliding model guidance law is designed in the terminal stage. In the terminal stage, target maneuver and coupling term of sight angle are estimated by three order extended state observer. Transition conditions of each guidance law are also given.Another typical trajectory feature of near space hypersonic vehicle is jump-like maneuvering. To intercept target of this kind, the first step, the gradient of target jump range is introduced to estimate its maneuverable capability. An adaptive sliding mode reaching law varying with the gradient of target jump range and the distance between missile and target is designed. The second step, the allocation strategy of reaction-jet/aerodynamic multi-control is designed and trajectory-control lateral-jets control technology is used in the terminal phase. By which the maneuvering ability of interceptor is ensured and the jump-like maneuver target is hit accurately.Secondly, in order to make full use of the cooperative efficiency of missile guidance and control system, integrated design of missile guidance and control is conducted based on Backstepping and Lyapunov redesign method. In the first place, the problem of normalizing the thrust vector and aerodynamic force is resolved. Based on the introduction of equivalent elevator angle, multiple inputs control problem has been transformed into a single input problem. Next, on the basis of the simplified and standardized model of attack-defense confrontation, integrated guidance and control is designed using Backstepping and Lyapunov redesign method and the law of integrated guidance and control has been got. Contrast this method with the traditional method which is consist of PN guidance law and PID control law, the results show that this method is effective.Finally, in order to carry out coordinated combat of multiple missiles to multiple targets, and intercept numerous near space hypersonic vehicles at the same time. At the first, the mathematic model is established which requires to maximum total intercept probability and to minimum total attack time. Genetic algorithm is used for dynamic task allocation. Then, for each group of results obtained from the task allocation, the best coordinated interception time is set up. The 4-D impact time control guidance law(ITCG) is designed in the forepart of interception based on theory of sliding mode control to ensure that intercept time are basically identical. Pure PNG law is adopted in the terminal phase to ensure that cooperative interception is accurate.