rocket engine

As one of the few advanced countries in liquid propulsion, France actually began to study and develop liquid rocket engine on the morrow of World War II.

法国是开展液体推进技术研究较早的国家之一，也是当前世界上液体推进技术比较先进的一个国家，但他们在这一领域也经历了一个漫长曲折的发展过程。

The result of analysis provides a basis for the application of composite material on rocket engine.

通过这些计算和分析,为复合材料在超远程弹药上的应用提供参考依据.

The feed system of a rocket engine may be the cause of undesirable oscillations.

火箭供应系统可能是有害的振源.

Hybrid propellant rocket engine

混合推进剂火箭发动机

Thermal control for platelet transpiration cooled preburner of liquid rocket engine using liquid oxygen

液体火箭发动机层板式预燃室液氧发汗冷却热控制

The degassing unit consisting of an injector and an overload box is equipped in the liquid propellant rocket engine of a coastal defence missile.

某海防导弹液体火箭发动机装置中，采用引射器加过载箱组成的除气机构。

Measurement technology of thermocouple sensor in the liquid rocket engine test

液体火箭发动机试验热电偶传感器测量工艺

Theoretical specific impulse for two-phase flow in nozzle of rocket-ramjet engine& a simple estimation method

火箭冲压发动机喷管的两相流动理论比冲&一种简单估算方法

A fault detection system for a liquid propellant rocket engine was proposed in the realtime conditions using the back propagation ( BP) neural network.

应用BP神经网络，提出了一种液体火箭发动机故障实时检测系统。

Nozzle optimization of liquid rocket engine based on CFD

基于CFD的液体火箭发动机喷管型面优化

Milling grooves on aerospace rocket engine-nozzle surface is an important process.

铣槽加工是大型航天火箭喷管制造中的关键工序.

Fault diagnosis of liquid rocket engine based on immune Agent

基于免疫Agent的液体火箭发动机故障诊断

The performance characteristics, structure and working cycle of pulse detonation rocket engine ( PDRE ) were introduced firstly.

摘要阐述了脉冲爆震火箭发动机 ( PDRE ) 性能特点 、 结构和工作过程.

Environmental factor of Weibull distribution for liquid rocket engine failure

液体火箭发动机失效的Weibull分布环境因子

Disigning coolant channel on the firebox of liquid rocket engine to loxodrome ( equal-angle helix) groove can improve firebox coolant capability greatly.

将液体火箭发动机燃烧室的冷却通道设计为斜航线（等倾角螺旋线）槽形，可以大幅度改善燃烧室的冷却性能。

Review of combustion instability testing research on liquid propellant rocket engine

液体火箭发动机燃烧不稳定性试验研究简述

Mo nozzle for the rocket engine nozzle professional.

钼喷嘴专业用于火箭发动机喷嘴.

For one thing, they simplify the design of a rocket engine.

首先, 它们可以简化火箭发动机的设计.

The Application of Reliability Increasing in the Manned Spaceflight Rocket Engine

可靠性增长技术在载人航天发动机研制中的应用

The leak of Liquid Rocket Engine ( LRE ) is very common and dangerous.

液体火箭发动机的泄漏是常见和极其危险的故障.

With a tremendous roar from its rocket engine, the satellite is sent up into the sky.

随着火箭发动机发出的巨大的轰鸣声, 卫星被送上了天空.

The BRABUS ROCKET engine and the entire drivetrain is operated high-performance lubricants from technology partner ARAL.

是Brabus火箭发动机和传动系统的整个运作高的技术合作伙伴咸海高性能润滑油.

Firstly, the principle, components and control of variable thrust rocket engine are discussed. Then, the regulating ways and the adoptable technologies of thrust are studied, and the applications in astronavigation are analyzed.

论文首先阐述了变推力火箭发动机的工作原理、组成与控制，研究了推力调节途径和可采用的技术手段，并对它在航天领域的应用进行了分析。

A new modular method is proposed for static simulation of liquid rocket engine.

提出了一种新的液体火箭发动机静态仿真模块化计算方法.

The complex flow was simulated with sequential and parallel SIMPLE algorithm in the combustion chamber of liquid rocket engine.

用串行和并行SIMPLE算法对液体火箭发动机燃烧室内的复杂流动进行了数值模拟。

The development process of reliability increasing of manned spaceflight rocket engine was overviewed by several kinds of technologies, including reliability analysis and design, reliability trial, reliability management. The methods are beneficial to other engines in the field of reliabilities increase studies.

本文运用可靠性分析及设计技术、可靠性试验技术和可靠性管理技术对载人航天发动机可靠性增长研制过程进行了综述，对其它型号发动机开展可靠性增长研究有一定的借鉴作用。

The research result has some reference values to rocket engine research institute building and strategy development.

其研究结果,对火箭发动机科研机构的建设及发展有一定的参考价值.

Unlike a rocket engine , the jet engine , as you konw, is an " air breather ".

正如你们所知道的, 这种喷气发动机与火箭发动机不同:它是 “ 空气喷气发动机. ”

Unlike a rocket engine , the jet engine , as you know, is an " air breather ".

正如你们所知道的, 这种喷气发动机与火箭发动机不同:它是 “ 空气喷气发动机 ”.

Through two methods measuring cutoff thrust and pressure of com-bustion chamber when testing liquid propellant rocket engine on ground, cu-toff impulse as simulated altitude condition is obtained. These methods are revie-wed simply, too.

本文叙述在地面条件下试验液体火箭发动机时，通过测量发动机后效段推力与测量发动机燃烧室压力两种方法来求得模拟高空后效冲量，并对这两种方法作简单评论。