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In this paper, the longitudinal linear control model of static unstable missile is established, and the longitudinal aerodynamic parameters and related symbol definitions of the missile are given. The structural model of the acceleration feedback autopilot is established, and the parameter design of the autopilot is carried out by combining the analytical method and the pole-placement algorithm, and the relevant design parameters are obtained. The simulation of different characteristic points of static unstable missile shows that the proposed autopilot has strong robustness. At the same time, it is concluded that the performance of the acceleration feedback autopilot of the static unstable missile will change with the change of the design frequency and the position of the accelerometer.
Liu et al. (Sun,) studied this question.