1) hybrid rocket motor
固液火箭发动机
1.
Investigation on pyrolytic product distribution of low density polyethylene of hybrid rocket motor;
固液火箭发动机燃料LDPE热解产物分布研究
2.
Effects of combustion chamber structure on combustion and flow of hybrid rocket motor;
燃烧室结构对固液火箭发动机燃烧与流动的影响研究
3.
Research on Working Process of the 85% H_2O_2-PE Hybrid Rocket Motor;
85%H_2O_2-PE固液火箭发动机工作过程研究
2) hybrid rocket
固液火箭发动机
1.
In order to know combustion process of hybrid rocket,pyrolysis test of solid fuel was carried out by using hot-plate heat conduction mode,then chemical kinetic parameters of solid fuel were obtained.
为了认清固液火箭发动机混合燃烧过程,采用热平板导热方式对固体燃料进行热分解实验,得到了固体燃料的化学动力学参数。
2.
Remarkable advantage such as low costing, high security, high reliability, low exhaust plume signal characteristic and environment non-pollution, which does not belong to Solid Rocket Motor (SRM) or Liquid Rocket Engine (LRE), advances astronautic experts to have much more interest in Hybrid Rocket Motor (HRM).
固液火箭发动机在成本控制、安全性、可靠性，排气羽流信号特征、环境等方面的优良特性，越来越受到国内外航天专家的重视。
3) solid-liquid rocket engine
固-液火箭发动机
4) Solid liquid rocket ramjet engine
固液火箭冲压发动机
5) Lithergol rocket engine
液固混合火箭发动机
6) hybrid rocket motor
固液混合火箭发动机
1.
Computation of fuel regression rate in classical hybrid rocket motors;
固液混合火箭发动机固体燃料的燃速计算
2.
Experimental study on hydrogen peroxide and polyethylene hybrid rocket motors;
H_2O_2-PE固液混合火箭发动机试验研究
3.
Numerical solutions of full Navier-Stokes equations were obtained for a nozzle two-phase flow of the nitrous oxide(N2O)/hydroxyl-terminated polybutadiene(HTPB) based fuels hybrid rocket motor.
利用二维轴对称N-S方程对选用氧化亚氮/丁羟基燃料推进剂的固液混合火箭发动机的喷管两相流进行了计算。
补充资料：光子火箭发动机
靠电磁辐射量子(光子)的定向流产生推力的火箭发动机。这种发动机在理论上具有最高的效能和比冲，它的主要结构部件是光子源。为了在光子源中获得足够大的光压，需要有50000～250000K的高温。这种发动机尚处于理论探索阶段。
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