Some units were fitted with the Type 68 19-tube 130mm multiple rocket launcher.
一些单位配备有68型19管130毫米多管火箭发射器。
This paper established the internal ballistics equation for the high-low pressure launcher with tandem construction when the rocket motor is ignited in the launch tube.
本文建立了火箭发动机在管内点燃情况下，串联结构的高低压无后座力发射器的内弹道方程，并对试验弹进行了数值计算。
The posture of a rocket in launch tube was calculated and analyzed Basel on the theory of non-linear transient dynamics.
以非线性瞬态动力学理论为基础，计算和分析了某型火箭发射过程中管内姿态情况。
According to analyze the structure of survival rocket and identify its vulnerable spots, necessary structural improvements are put on overall lock and the hermeticity of igniter tube.
通过对火箭包的结构进行分析，确定薄弱环节，对整体防松和点火管密封性进行了必要的结构改进。
The four Type 62 five-tube AS rocket launchers on the bow deck were replaced by two improved Type 87 6-tube AS launchers, which features automatic reloading.
位于艏甲板上的四具62型五管as火箭发射装置被二具改进87型六管as发射装置替代，特点是自动再装填。
Taking the impact jet flow field of individual rocket as research object, this paper calculates the jet flow field near the back of the launching tube by using the numerical simulation method.
该文以单兵火箭冲击射流流场为研究对象，采用数值模拟技术，对定向器管尾附近区域的燃气流场进行了数值计算，给出了发动机工作早期阶段冲击射流噪声场形成过程的计算结果。
Taking the impact jet flow field of individual rocket as research object, this paper calculates the jet flow field near the back of the launching tube by using the numerical simulation method.
该文以单兵火箭冲击射流流场为研究对象，采用数值模拟技术，对定向器管尾附近区域的燃气流场进行了数值计算，给出了发动机工作早期阶段冲击射流噪声场形成过程的计算结果。
应用推荐