1、

In this paper, using the method of numerical simulation, is studied the forming process of flow field structure in a stepped rocket launcher tube when a supersonic jet exhausts into the tube.

本文以数值模拟为手段,研究了超音速燃气射流喷入阶梯型火箭发射管后,管内流场结构的发展过程。

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2、

The strength research of the rocket launcher GFRP tube

玻璃钢制火箭炮定向器的强度研究

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3、

The internal ballistics and the throttling performance of 85% H2O2-PE hybrid rocket motor loaded with tube grain are studied. The hot firing data of two test motors have been carefully analyzed.

研究了管型药柱的85%H2O2-PE固液火箭发动机的内弹道性能和节流特性,分析了两台发动机的试验结果。

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4、

The time history of angular rate includes three stages which are rocket moving in tube, exhausted flow impacting and free vibration after impacting.

其时间历程包括发射时弹体在管内运行、燃气对定向器束冲击及冲击后定向器束自由振动的振动角速率。

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