论文部分内容阅读
装备有压力和加速度传感器的战术导弹挂在战斗机上进行飞行试验，以便有助于描述载飞环境。高攻角切断油门时的压力数据用两种技术进行分析。分析显示，沿导弹的窄频随机力的对流几乎相同，表明这是一种强相干空气动力学结构。已测压力的标准偏差的环形分布似乎表明，存在着与尾迹涡系有关的涡流。在考虑和不考虑空气动力激励范围内的相关性（对流和旋涡）两种情况下，用有限元法对导弹的横向振动进行了分析。在某些频率范围内，这些效应可能非常重要。
Tactical missiles equipped with pressure and acceleration sensors were hung on fighter jets for flight tests to help describe the loading environment. The pressure data at the high angle of attack when cutting the throttle is analyzed using two techniques. The analysis shows that the convection over the narrow-frequency stochastic forces along the missile is almost the same, indicating that this is a strongly coherent aerodynamic structure. The circular distribution of the standard deviation of the measured pressures seems to indicate that there is a vortex associated with wake vortices. In both cases of considering and not considering the correlation (convection and vortex) in aerodynamic excitation range, the transverse vibration of missile was analyzed by finite element method. These effects can be important in some frequency ranges.