Research And Design On The Guidance Law Of Attacking Maneuvering Target

Guidance law is an important issue for the design of missile guidance and control system, and also is the key technology of the precision-guided weapons to achieve tracking and intercepting targets. With the development of modern weapons technology, the maneuvering ability of the target grows more and more strong. The traditional guidance law is difficult to meet the requirements, we must seek new theories and research methods to design the guidance law which meets the requirements.Relying on the research background, this paper gradually expands on the research and design work for the uncertainty, maneuverability, nonlinear coupled, such difficult design problems of guidance law caused by maneuvering targets. The two-dimensional and three-dimensional relative movement model between the missile and target are built based on the previous work at first, then the equations describing the relative movement are given.By selecting the appropriate state variable, the relative motion equation is converted to the system state equations. Using Lyapunov stability theory, backstepping design method and selecting the appropriate form of control law, and twice stabilization for the system state variables, derived a nonlinear robust guidance law. Using the basic conclusions of variable structure control theory and the variable structure control method of discrete systems, and taking the missile-target relative velocity deflection angle as the sliding surface, derived a discrete sliding mode guidance law. Taking the numerical simulations for each of guidance law, the numerical simulation results show that the guidance law designed can meet the designing requirements and be robust to attacking maneuvering targets.