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在超音速风洞中进行了从母导弹有控制抛撒子导弹的试验。具有不同刚度、质心和铰支释放角的截头锥形蒙皮板块,用行程和压力可调的预加载压缩气体作动器弹出。蒙皮板块依靠用电脉冲切断的箍紧带释放。用测系留子导弹轨迹的尾支架系统和用拍摄弹入气流内的子导弹运动过程的方法,获得了子导弹的运动轨迹。弹射速度用伸缩杆式的压缩气体作动活塞控制,而预加载活塞的释放靠爆炸约束螺栓实现。子导弹的弹射程序实现了计算机程控。这些数据可用于设计全尺寸的子导弹抛撤系统。
Experiments were conducted in supersonic wind tunnels with controlled missile launchers from mother missiles. Frustrated conical skin panels with different stiffness, centroid, and hinge release angles are popped up with a pre-loaded compressed gas actuator with adjustable stroke and pressure. The skin flap is released by the banding cut off by the electrical pulse. The trajectory of the sub-missile was obtained by using the tail-bracket system of the tethered missiles and the shooting process of the sub-missiles launched into the air stream. The ejection speed is controlled by a telescopic rod-type compressed gas actuator piston, and the release of the pre-loaded piston is achieved by an explosion restraining bolt. Missile missile ejection program to achieve a computer program-controlled. These data can be used to design a full-size sub-missile ejection system.