1) Impulse rocket engine
脉冲式火箭发动机
2) multi-pulse solid rocket motor
多脉冲火箭发动机
1.
Aiming at tensile and compressive modulus characteristics of ceramic hatch of multi-pulse solid rocket motor,a 2D axisymmetric finite element model was derived by ANSYS software.
针对多脉冲火箭发动机用陶瓷舱盖材料拉压模量不同的特性,利用ANSYS软件建立了平面轴对称有限元模型,分析了隔舱接触面上的压力与摩擦力对舱盖危险点应力的影响。
3) pulse detonation rocket engine
脉冲爆震火箭发动机
1.
Numerical simulation of converging-diverging nozzle flow in pulse detonation rocket engine;
脉冲爆震火箭发动机收敛扩张喷管数值模拟
2.
Investigation on two-phase pulse detonation rocket engine with solenoid valve;
电磁阀式两相脉冲爆震火箭发动机试验
3.
A pulse detonation rocket engine(PDRE) is a new propulsion system that generates thrust by using high-temperature and high-pressure air produced by pulse detonation waves.
脉冲爆震火箭发动机是一种利用脉冲式爆震波产生高温、高压燃气发出的冲量来产生推力的新型推进系统。
4) pulse detonation rocket engine(PDRE)
脉冲爆震火箭发动机
1.
We present the experimental system of a pulse detonation rocket engine(PDRE) and perform an experiment on its thrust change with that of equivalence ratio using kerosene as fuel and oxygen as oxidizer at the equivalence ratio between 0.
简述了脉冲爆震火箭发动机(PDRE)的实验系统,在12 Hz的频率下,以煤油为燃料,以氧气为氧化剂,进行了当量比在0。
2.
A prototype of pulse detonation rocket engine(PDRE)is introduced to solenoid valves for the control of oxygen,kerosene and isolation gas;thus continuous combustion is avoided.
简述了脉冲爆震火箭发动机的实验系统,利用电磁阀控制煤油,氧气和隔离气体,避免了连续燃烧。
3.
The pulse detonation rocket engine(PDRE)with variable cross-section was investigated using kerosene as fuel and oxygen as oxidizer at the equivalence ratio 1.
0的条件下,进行了变截面脉冲爆震火箭发动机的实验研究,其中包括等截面发动机,扩张型发动机,收敛型发动机,扩张-收敛型以及收敛-扩张型发动机。
5) Dual pulse solid rocket motor
双脉冲固体火箭发动机
6) pulse solid rocket motor
脉冲固体火箭发动机
补充资料：活塞式航空发动机(见航空发动机)
活塞式航空发动机(见航空发动机)
piston aeroengine
huosaishi hQngK。，;，，。一口，活塞式航空发动机(piston aeroengine)~，、八中二九士几
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