分析了带有舵面及控制系统的战术导弹的气动伺服弹性稳定性。动力学方程中包含弹体的一阶弯曲振动、弹体的刚体平动和转动 ,可控舵面只考虑刚体偏转。用细长体理论和气动导数方法计算了导弹的非定常气动力 ,两种方法均适用于亚音速和超音速情况。采用 Nyquist方法和 Bode图方法分析了某导弹的气动伺服弹性稳定性和稳定裕度 ,两种气动力方法所得结果一致。 The aerodynamic servo elastic stability of the tactical missile with the control surface and control system is analyzed. The dynamic equation contains the first-order flexural vibration of the projectile, the rigid body of the projectile translates and rotates, and the controllable surface only considers the deflection of the rigid body. The slender body theory and the aerodynamic derivative method are used to calculate the unsteady aerodynamic forces of the missile. Both methods are suitable for subsonic and supersonic conditions. Nyquist method and Bode plot method are used to analyze the aerodynamic stability and stability margin of aero-missile. The results obtained by the two aerodynamic methods are the same.