导弹气动伺服弹性稳定性分析

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。

Aeroservoelastic stability of missile

Aeroservoelastic stability of a missile with rudders and control system is analyzed in this paper. The first body bending vibration, rigid plunging motion and rotation of the body are concerned. Controlled rudder is regarded as rigid body. The unsteady aerodynamics on body are dealt with two quasi steady aerodynamics theories(i.e. slender body method and subsection aerodynamics derivative method which are applicable to subsonic and supersonic flight conditions). Aeroservoelastic stability of the missile and stability margins are analyzed and compared using Nyquist method and Bode graph method in frequency domain. Both aerodynamics methods get the same result.