1) pulse detonation engine
脉冲爆震发动机
1.
Numerical investigation of multi-tube pulse detonation engine with common nozzle;
共用尾喷管多管脉冲爆震发动机数值模拟研究
2.
Exprimental investigation of integrating pulse detonation engine system;
脉冲爆震发动机模拟发射实验研究
3.
Experimental investigation of air-breathing valveless pulse detonation engine;
吸气式无阀脉冲爆震发动机试验研究
2) Pulse detonation engine(PDE)
脉冲爆震发动机
1.
Numerical simulation of the flow field of multicycle pulse detonation engine(PDE) is helpful for understanding the engine principle and performance analysis,and can provide the useful information for PDE design.
针对二维带有收敛扩张喷管的脉冲爆震发动机模型,采用带基元化学反应的Euler方程组和H2、空气的9组分20基元反应,对发动机在前六个工作循环的流场进行了数值模拟。
2.
To improve the reliability of pressure measurement in detonation combustor of pulse detonation engine(PDE),the pressure/time curves of detonation were measured at single detonation and multicycle detonation,respectively,by using a dynamic pressure measurement system.
为了提高脉冲爆震发动机(Pulse Detonation Engine,简称PDE)内爆震波压力测量值的可靠性,解决多循环PDE爆震室压力测量问题。
3.
The results show that all nozzles can augment the thrust of baseline pulse detonation engine(PDE)and there is an optimal nozzle area ratio where thrust augmentation is maximized.
选取3类10种有代表性的脉冲爆震发动机尾喷管进行了试验。
3) pulsed detonation engine
脉冲爆震发动机
1.
A new device system was developed to measure the pulsed temperature and vapor concen- tration in the exhaust flow during the multicycle process of pulsed detonation engine.
本文采用新型研制的脉冲温度和水蒸气浓度测量仪测量了吸气式脉冲爆震发动机多循环工作过程中的尾焰温度,结果表明该测量仪不仅能够很好地捕捉每一个脉冲温度,与热成像仪测量的结果比较证明其测量温度在误差范围内。
4) pulse detonation engine(PDE)
脉冲爆震发动机(PDE)
1.
A pulse detonation engine(PDE) with diameter and length of 61mm and 1140mm respectively,was used to get the heat loads of detonation tubes which were designed into two types.
在一台内径61 mm、长度1140 mm的气动阀式脉冲爆震发动机(PDE)上,进行了爆震管热负荷的测量计算,主要采用了两种换热模型:一是自然对流和热辐射模型;二是强迫对流模型。
5) 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。
6) 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。
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