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分析了某类导弹系统的稳定性，研究了天线罩瞄准线误差斜率Ａ的摄动对寻的制导控制系统的影响。此影响只与天线罩瞄准线误差斜率的摄动量、导弹耦合回路传递函数的分子和弹体气动力时间常数有关。分析了天线罩误差对导引控制器设计的限制，得出了导引控制器设计的边界条件。对一类真实导弹模型（非线性时变模型）的试设计证明，对于超过此边界值的情况，很难设计出满足性能要求的导引控制器。
The stability of a missile system is analyzed. The influence of the perturbation of slope a of the radome on the guidance error of the guidance system is studied. This effect is only related to the perturbation of the error slope of the line of sight of the radome, the numerator of the transfer function of the missile’s coupling loop and the aerodynamic time constant of the projectile. The limitation of the design of the guidance controller by the radome error is analyzed and the boundary conditions of the guidance controller are obtained. A trial design of a true missile model (a nonlinear time-varying model) proves that it is difficult to design a guidance controller that meets performance requirements beyond this boundary value.