考虑滚仰导引头寄生回路的旋转导弹驾驶仪稳定性设计

For the problem that the parasitical loop of roll-pitch seeker affects the dynamic stability of spinning missile, the disturbance rejection rate model of roll-pitch seeker and the mathematical equation of spinning missile are established, and the cross-coupling effect of control system induced by the rotation motion of missile body is derived and analyzed. The relationship between the autopilot gain coefficients and the expected frequency or damping is formulated. The sufficient and necessary condition for the dynamic stability of spinning missiles is analytically derived by stability analysis. The dynamic stability of spinning missile under various conditions is studied by numerical simulations. The results indicate that the stability of spinning missiles is closely related to the disturbance rejection rate and rolling rate of roll-pitch seeker, and the design indices of autopilot. The stability region of design frequency of spinning missile autopilot is obvisously smaller than that of the non-spinning missile, and the low rolling rate is helpful to reduce the effect of parasitic loop of roll-pitch seeker on the stability of spinning missile.