某战术导弹舵面异常高频抖动机理分析

Study on Anomaly Oscillation Mechanism of Control Surface of a Tactical Missile

通过CFD数值模拟分析某战术导弹舵面高频抖动机理。该导弹采用正常式气动布局,舵面靠近弹尾,发动机喷管位于弹体底部中央。在亚音速飞行试验中,固体发动机工作结束时,舵面出现异常高频抖动现象,机理不明。数值模拟分析结果表明:发动机工作结束时,弹体底部非定常分离流动随着发动机尾喷流减弱而增强,舵面在弹体底部非定常气动力激励下高频抖动。

To study anomaly oscillation mechanism of control surface of a tactical missile has been carried out by CFD method.Normal aerodynamic configuration was used in the tactical missile whose control surface was near the missile tail and the jet of the motor was at the center of bottom of the missile.In the course of flight test,anomaly oscillation of control surface occurred when solid rocket motor was over.But the mechanism is unknown.So CFD analysis was carried out.The results show that the separated flow enhances with jet flow is weakened when the motor is almost over,so control surface oscillates at high frequency under the motivation of unsteady aerodynamics.The result of analysis and method of numerical simulation would be referenced in optimal design of similar Missile.