Establishment and Simulation of Error Model for Interceptor's Terminal Guidance Phase

Six-degree of freedom equations are described for high-speed interceptor flying in extra-atmospher- ic space.Taking some errors including inertial components' error,seeker's angular error,dynamical equipment's error and excursion of centroid into consideration,the error model of interceptor in terminal guidance phase is con- structed.The amendatory proportional navigation(PN)law is designed to compensate normal-needed overloading rapidly.Moreover,interceptor's attitude is always regulated to track the Line-Of-Sight.Simulation results vali- date the rationality of this error model and the attitude stabilization can be satisfied to realize efficiently the terminal guidance of interceptor as well as precision demand.