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1)  Integral solide propellant rocket ramjet engine
整体式固体火箭冲压发动机
2)  Integral rocket ramjet
整体式火箭冲压发动机
3)  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
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 ducted rocket
固体火箭冲压发动机
1.
Modeling and simulation on the gas generator and gas control valve of solid ducted rockets;
固体火箭冲压发动机燃气发生器及燃气流量调节阀建模及仿真
2.
Three dimension numerical simulation on air inlet of solid ducted rocket;
固体火箭冲压发动机进气道三维数值模拟
3.
Dynamic modeling and model reduction order of controllable flow solid ducted rockets;
燃气流量可控的固体火箭冲压发动机动态建模及模型降阶(英文)
补充资料:冲压式火箭用高能固体推进剂
分子式:
CAS号:

性质:指由含能黏合剂、高能添加剂组成的贫氧高能推进剂。如由缩水甘油基叠氮聚合物(GAP)配合B,Al,Mg,Zr等添加剂,构成的高能推进剂装填于冲压式火箭发动机第一级燃烧室。当空气/燃料比为14时,第二燃烧室的比冲可达7644Ns/kg,燃烧效率达90%以上。

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