Design for terminal guidance law of combined control interceptor in aerosphere

A terminal guidance law is presented to intercept target in aerosphere. The mathematical model of combined control interceptor constructed using second Newton law and moment of momentum theorem is presented. Based on this model, the equations of relative movement between interceptor and target are. constructed. In order to reduce the influence from the chattering and maneuverable target, a three-dimensional fuzzy inference system is designed to tune the variable structure guidance law. Due to this guidance law needs no information on. maneuverable motion of target, it is convenient for practical project. Simulation results show that this guidance law reduces the influence from the chaffering and maneuverable target, and implements efficiently the precise guidance of interceptor as wen as preferable robust stability, which shows the veracity and advantage.