Influence of seeker disturbance rejection rate on missile guidance system

Spring torque and damping torque are two main factors which cause seeker disturbance rejection rate problems, for studying the influence of seeker disturbance rejection rate on the guidance system of missile, a model of the guidance system which contains seeker disturbance rejection rate parasitical loop was established; the relationship between the disturbance rejection rate and the stabilization of the guidance system was analyzed on basis of the model; under the typical noise input condition of radar seeker, the simulation gave the miss distances of missile corresponding to different seeker disturbance rejection rates. The results show that the guidance system parameters greatly affect the parasitical loop stability zone; the larger the disturbance rejection rate caused by spring torque, following the reduction of the distance between missile and target, the earlier the radiation of the guidance system. The larger the disturbance rejection rate caused by damping torque, the later the radiation of the guidance system; under the condition of seeker noise input, the larger the disturbance rejection rate caused by spring torque, the larger the miss distance. The larger the disturbance rejection rate caused by damping torque, the smaller the miss distance. The conclusion may provide theoretical instruction for the general missile design and the demonstration for the relevant indices of seeker.