1) solid propellant ramjet
固体冲压发动机
1.
Study on the C/SiC composites for hot gas valve of solid propellant ramjet;
固体冲压发动机燃气阀用C/SiC复合材料研究
2) solid rocket ramjet
固体火箭冲压发动机
1.
Quick-forecasting algorithm for performance of solid rocket ramjet;
固体火箭冲压发动机性能快速预估算法
2.
Some technological problems of solid rocket ramjet;
固体火箭冲压发动机的若干技术问题
3.
Experimental study on solid rocket ramjet with central air-inlet mode;
中心进气式固体火箭冲压发动机试验研究
3) solid fuel ramjet
固体燃料冲压发动机
1.
Analysis on thrust stationarity and flight stability of solid fuel ramjet;
固体燃料冲压发动机推力平稳性及飞行稳定性分析
2.
Influence of vortex on performance of solid fuel ramjet;
涡流对固体燃料冲压发动机性能影响分析
3.
Structure design on torch igniter of solid fuel ramjet;
固体燃料冲压发动机火炬式点火器设计
4) ducted rocket motor
固体火箭冲压发动机
1.
There are a variety of influential factors to the combustion efficiency of secondary chamber of boron-based propellant ducted rocket motor,which are difficult to be expressed accurately by analytical functions.
影响含硼推进剂固体火箭冲压发动机补燃室燃烧效率的因素很多,且各因素对燃烧效率的影响很难用精确的解析函数式来表示。
5) solid ducted rocket motor
固体火箭冲压发动机
1.
Erosion test of the insulation in the ramjet combustor of solid ducted rocket motors;
固体火箭冲压发动机补燃室绝热层烧蚀试验研究
2.
The 3D reaction flow field in the afterburning chamber of solid ducted rocket motor with binary dual-underside inlet mode was numerically simulated by means of RNG κ-ε turbulence model and one step eddy-dissipation combustion model.
采用RNGκ-ε湍流模型及单步涡扩散燃烧模型,对二元双下侧进气式固体火箭冲压发动机补燃室内三维反应流场进行了数值模拟,得到了补燃室二次燃烧效率的变化趋势。
3.
By direct-conncted simulation calculation,the effects of common heater fuel (hydrogen,kerosene,methane and alcohol) on performance of solid ducted rocket motor with low-oxygen boron-based propellant were investigated.
通过直连模拟计算,研究了常用加热器燃料(氢气、煤油、甲烷和酒精等)对含硼贫氧推进剂固体火箭冲压发动机性能的影响。
6) Solid fueled ramjet
固体燃料冲压发动机
1.
Based on theorctical analysis of mean burning rate in solid fueled ramjet (SFRJ),the exponcntialrelationship between burning rate and chamber diameter and pressure is established through numerical simula-tion.
在固体燃料冲压发动机（SFRJ）平均燃速理论分析基础上，通过数值摸拟，得出燃速与燃烧室直径和压强的指数表达式。
2.
Simple reacting flow model of solid fueled ramjets based on Arrenius formula and viscosity hydrodynamics is established and used to simulate an experimental ramjet.
建立了基于阿累尼乌斯公式和粘性流体力学的固体燃料冲压发动机（ＳＦＲＪ）简单反应流模型，并在该模型下对某实验发动机进行了模拟，得出了燃烧剂组分、燃速、温度等发动机参数的变化趋势，给出了一些有用的结论。
补充资料：航空发动机推重比(见航空发动机推力)
航空发动机推重比(见航空发动机推力)
thrust to weight ratio of aeroengine
hQngkong角dong)1 tuizhongbi航空发动机推重比〔thros*:。wdgh:ra-tio of aeroengine)见航空发动机推力。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条