China has undertaken to research and develop composite solid propellant rocket motors since 1958.
中国从1958年开始复合固体推进剂火箭发动机的探索和研制工作。
A conception of adjustable solid propellant rocket motor was proposed.
本文提出了一种推力可调的固体火箭发动机的设想方案。
A new method of the solid propellant rocket nozzle design is presented.
本文介绍一种设计固体火箭喷管的新方法。
The 300mm diameter solid propellant rocket motor employs a composite propellant end burning grain.
直径300毫米的固体推进剂火箭发动机采用了复合推进剂端燃药柱。
This paper discusses operating principles and technology challenges of the integral solid propellant rocket ramjet.
研讨了整体式固体冲压火箭发动机的工作原理及技术难点；
The ablation mechanism and the performance of carbon-phenolic material of solid propellant rocket nozzles are studied.
本文研究了碳-酚醛材料在固体火箭发动机喷管中的烧蚀机理及性能。
Overload acceleration is one of those important factors which influence the performance of solid propellant rocket motor.
过载加速度是影响固体火箭发动机性能的重要因素之一。
In this paper, one-dimensional two-phase constant lag flow in combustion chamber of solid propellant rocket motors is described.
本文论述了固体火箭发动机燃烧室一维两相常滞后流动。
Interface bond quality of solid propellant rocket motor can be tested by Lamb waves, but the modes of Lamb waves need to be selected.
用兰姆波可对固体火箭发动机进行胶接质量的检测，但需要对其模式进行选择。
According to the entire design requirements and restraints of a certain solid propellant rocket motor, design method of nozzle contour is put forward.
根据某型号固体火箭发动机总体设计要求及限制条件，给出了喷管型面设计方法。
The plume temperature is an important parameter, for solid propellant rocket engines and it is useful for determining the combustion process of the engine.
推进剂的羽焰温度是固体推进剂火箭发动机的重要参数，对于研究发动机内的燃烧过程具有重要价值。
High speed rotation solid propellant rocket motor recording apparatus which we designed is going to resolve pressure testing of rocket motor in high speed rotation.
本文设计的高速旋转固体火箭发动机内置动态参数记录仪，着重解决火箭发动机在高速旋转状态下压力测试问题。
The temperature of a high temperature, high pressure plume solid propellant rocket engine is difficult to measure but is useful for determining the combustion status of the engine.
对于固体火箭发动机羽焰温度的测量是困难的，了解其温度分布对于研究发动机内燃烧流场的特性有重要价值。
The temperature of a high temperature, high pressure plume solid propellant rocket engine is difficult to measure but is useful for determining the combustion status of the engine.
对于固体火箭发动机羽焰温度的测量是困难的，了解其温度分布对于研究发动机内燃烧流场的特性有重要价值。
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