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On the issue of low stability of parasitic loop caused by seeker disturbance rejection rata and radome boresight error slope in situations of high altitude and low velocity pressure, a guidance control related design method is presented. First, the linear model of parasitic loop of an active-radar guided surface-to-air missile is established, and the stability is analyzed. Second, a guidance control related design method is presented; effects of parasitic loop are considered while designing the autopilot. Simulation results show that the designed autopilot can greatly improve stability of parasitic loop and reduce the demands of radome boresight error slope.