Design Of Guidance Law For Intercepting Hihg Speed Maneuvering Target

With the development of time and technology,The missile which as the product of the Second World War,has evolved to a multiple comprehensive and more destructive tool.In modern warfare,The traditional single guidance law has been unable to meet the diverse needs.Developed countries,currently have hypersonic cruise missiles,near space vehicles and reentry ballistic missiles and other air kill weapons which are characterized by high speed and mobility.In order to effectively implement the defense interception,The interceptor missile has to develop towards high-speed maneuvering interception.This paper will consider the finite time convergence rule,design a guidance law for intercepting high-speed maneuvering targets.On the basis of the nonmaneuvering target finite-time guidance law a nonlinear guidance law for intercepting maneuvering targets is proposed by combining integral sliding mode and generalized super-twisting(ST)algorithm.Lyapunov stability analysis shows that the proposed law possessess robustness against high-speed maneuvering targets.The maneuvering acceleration of different amplitudes and frequencies is simulated respectively.The simulation results confirm the properties of finite-time convergence and strong robustness and high precision of the system.Then,considering the dynamic characteristics of missile autopilot,and designing a finite time disturbance observer to estimate the acceleration information of maneuvering target.A nonlinear integral sliding surface related to the modified states is defined and a continuous finite-time guidance law is designed by means of parametrized ST algorithm and the estimate of the matched disturbance.The finite time convergence of the guidance law is proved by Lyapunov method.The simulation results that in different simulation conditions,The maneuvering acceleration of different amplitudes and frequencies is simulated respectively,The guidance law designed has high guidance precision...