为实现冷弹射导弹在二次点火时尾罩侧向抛离发射轴线的目的,提出一种新型抛罩方案:偏心尾罩与喷管出口之间通过密封塞连接,依靠燃气射流作为动力源实现侧抛分离。考虑不同质心位置及水平侧向风对分离过程产生的影响,建立了三维尾罩分离模型,结合重叠动网格技术,耦合求解流体控制方程及刚体六自由度运动方程,对尾罩分离过程进行数值模拟计算。获得了受射流冲击时尾罩运动特性变化曲线,以及尾罩对燃气射流流场产生的干扰特性。研究结果表明:该方案可实现尾罩侧向抛离发射轴线的目的。具体而言,随着质心偏置程度增大,有利于轴线处射流状态率先趋于稳定,当质心位置大于二分之一半径时,射流对尾罩产生加速转动效果大于平动,增加尾罩运动过程中的不稳定性,分离后期尾罩出现靠近轴线趋势;水平侧向风有利于尾罩远离轴线,且随着风速增大远离轴线趋势更明显。

In order to realize the purpose of the tail cover being side-thrown away from the launch axis during the second ignition of the cold catapult missile, a new type of shroud throwing scheme was proposed: the eccentric tail cover and the nozzle outlet were connected by a sealing plug, and the gas jet was used as the power source to realize the side-throwing separation. Considering the influence of different centroid positions and horizontal lateral winds on the separation process, a three-dimensional tail mask separation model was established, combined with the overlapping dynamic mesh technology, the fluid control equation and the rigid body six-degree-of-freedom motion equation were coupled, and the tail cover separation process was numerically simulated. The variation curve of the motion characteristics of the tail cover when it is impacted by the jet and the interference characteristics of the tail cover on the flow field of the gas jet are obtained. The results show that the scheme can achieve the purpose of lateral throwing of the tail cover away from the emission axis. With the increase of the degree of centroid bias, it is beneficial for the jet state at the axis to be stable first. When the centroid position is greater than one-half radius, the jet has a greater accelerating rotation effect on the tail cover than the translational rotation, which increases the instability of the tail cover during the movement, and the tail cover tends to be close to the axis in the later stage of separation. The horizontal lateral wind is conducive to the tail cover to stay away from the axis, and the trend of moving away from the axis is more obvious with the increase of wind speed.