rocket engine的例句大全

A sample of rocket engine thrust chamber with cooling channels was successfully manufactured by APEF.

成功制造出带冷却通道的火箭发动机推力室身部样件。

The primary analysis on heat transfer and pressure drop of the thrust chamber in hydrogen-oxygen-hydrocarbon tripropellant rocket engine

氢氧烃三组元发动机燃烧室传热、流阻初步分析

This paper presents the development of the liquid propellant rocket engine technology from the viewpoint of combustion chamber pressure, thrust level and power cycle.

本文从燃烧室压力、系统工作循环方式以及最大推力三个方面叙述了世界各国液体火箭发动机的技术水平。

A calculation method for the rocket engine's optimum thrust nozzle contour design

火箭发动机最佳推力喷管型线的计算方法

A study of the maximum solid rocket engine thrust nozzle surface for one-dimensional two-phase flows

固体火箭发动机一元两相流动最大推力喷管型面研究

Mechanical and Error Characteristics of Rocket Engine Thrust Vector Test System

火箭发动机六分力试验系统力学和误差特性

Design of High Efficiency Turbine with Large Tip Clearance for Rocket Engine

大叶顶间隙高效率火箭发动机涡轮设计

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

Attributing to the large flow rate, high efficiency level reaction turbine is adoptive in staged combustion cycle liquid rocket engine.

基于闭式补燃循环液体火箭发动机流量大的特点，欲设计效率水平高的航天反力式涡轮。

Pasty rocket engine' energy can be controlled.

膏体发动机具有良好的能量可控性。

TESTING Experimental investigation of pasty propellant rocket engine

膏体推进剂发动机试验

In the field of aerospace manufacturing, the processing of the spiral cooling channel, which is on the combustion chamber nozzle of liquid rocket engine, is a key technology.

在航天制造领域中，液体火箭发动机燃烧室喷管的螺旋式冷却通道加工是一项关键技术。

The Critical Exhaust-throat Area Ratio of Base-bleed Devices on Compound Rocket Engine with Integrative Base Bleed Function

底排-火箭复合发动机底排临界面喉比的确定

The Effect of Heat Shield on Temperature Distribution of Rocket Engine Thrust Chamber

隔热罩对火箭发动机推力室温度场的影响

A new type gasdynamic arming switch of rocket base fuze was studied, which closes the electronic delay arming device utilizing the gas from rocket engine.

新型燃气动力保险开关用于弹底引信，该机构利用火箭弹发动机燃气压力实现电子延期保险的接电。

Research on the data processing method of solid propellant rocket engine plume temperature

一种测量固体火箭发动机羽焰温度的数据处理方法研究

Nonlinear Dynamic Stability of Liquid Hydrogen Turbopump Rotor-S eal System in Rocket Engine

火箭发动机液氢涡轮泵转子-密封系统的非线性动力稳定性

A gas flow model with laser plasma as heat source was developed based on axial symmetric Euler equations in the laser propulsion rocket engine absorption chamber.

以轴对称非定常欧拉方程为基础，建立了激光推进火箭发动机吸收室内纯气相单组分、以激光等离子体为内热源的流场模型。

Point-to-point suborbital travel would require a different design, such as a blunter shape to better handle the higher speeds and heat of atmospheric re-entry, and a more powerful rocket engine.

点对点的亚轨道旅游需要一个不同的设计，如顿的形状更好的掌握速度但是进入大气温度却很高需要一个更强大的火箭发动机。

Primary analysis of deep cooled turbojet liquid rocket engine combined cycle

深冷涡喷火箭组合循环发动机初步分析