考虑滚仰导引头寄生回路的旋转导弹驾驶仪稳定性设计

针对滚仰导引头寄生回路对旋转导弹动态稳定性影响的问题，建立滚仰导引头隔离度模型和旋转导弹的数学方程，推导分析导弹弹体旋转运动对控制系统的交叉耦合效应，研究自动驾驶仪增益系数与期望频率或阻尼的关系，解析出旋转导弹动态稳定性的充要条件。采用数学仿真方法分析不同条件下的旋转导弹动态稳定性，并得到旋转导弹稳定性与滚仰导引头隔离度的幅值、滚转率和自动驾驶仪设计等指标之间的定量关系。结果表明，旋转导弹自动驾驶仪设计频率的稳定区域与非旋转导弹相比明显变小，低旋转速度有利于减小滚仰导引头寄生回路对旋转导弹稳定性的影响。

Stability Design of Spinning Missile Autopilot Considering Parasitical Loop of Roll-pitch Seeker

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.