介绍了基于计算流体动力学(CFD)的阻尼导数预测方法以及其在复杂带控制舵导弹外形的俯仰/滚转阻尼导数预测中的应用.方法采用求解三维非定常ALE(arbitrary Lagrangian-Eulerian)形式RANS(Reynolds-averaged Navier-Stokes)方程加湍流模型的方法得到模型强迫运动的气动力时间历程,再通过绕模型非定常运动过程得到的气动力迟滞曲线计算得到俯仰及滚转阻尼导数.为了验证采用数值方法的正确性,针对基本带翼导弹外形,采用强迫模型按正弦形式振动,计算得到了超声速范围内马赫数从1.5到2.5的俯仰及滚转稳定性参数,通过与风洞试验及弹道数据结果的比较发现,两者吻合较好. The damping derivative prediction method based on Computational Fluid Dynamics (CFD) and its application in the prediction of pitch / roll damping derivatives of complicated rudder missile with complex shape are introduced.METHODS The method of solving the three-dimensional unsteady ALE (arbitrary Lagrangian-Eulerian) RANS (Reynolds-averaged Navier-Stokes) equation and turbulence model are used to obtain the aerodynamic time history of model forced motion, and then the pitch and roll damping derivatives are calculated by the aerodynamic hysteresis curve obtained from the unsteady motion around the model. According to the correctness of the numerical method, the pitch and roll stability parameters of Mach number ranging from 1.5 to 2.5 in hypersonic range were calculated for the basic wing-shaped missile with the forced vibration model in sinusoidal form. Through the test with wind tunnel and the trajectory Data comparison results found that both agree well.