rocket engine
美 
英
- un.火箭發(fā)動機(jī)
- 網(wǎng)絡(luò)火箭引擎；火箭動力機(jī)；火箭發(fā)動機(jī)試驗
英漢解釋
英英解釋
例句
Unlike a rocket engine, the jet engine, as you know, is an "air breather" .
正如你們所知道的，這種噴氣發(fā)動機(jī)與火箭發(fā)動機(jī)不同：它是“空氣噴氣發(fā)動機(jī)”。
This alone is enough to give the disk lift and with the addition of the rocket engine its vertical acceleration would be extremely rapid.
僅此是不夠的，讓磁盤升降機(jī)及與增補的火箭發(fā)動機(jī)，其垂直加速度會非常迅速。
The rocket engine , with its steady roar like that of a waterfall or a thunderstorm , is an impressive symbol of the new space age .
火箭發(fā)動機(jī)以其類似于瀑布或大雷雨的持續(xù)轟鳴給人以深刻印象，成為太空新時代的象征。
The missile uses active radar homing and is powered by a solid rocket engine (with a solid rocket booster).
導(dǎo)彈使用主動雷達(dá)引導(dǎo)和動力由一臺固體火箭發(fā)動機(jī)（使用一臺固體火箭助推器）提供。
"So many bits of the rocket engine fall off that it would be dangerous to aircraft if [flights] were allowed. "
“會有那么多的火箭發(fā)動機(jī)碎片脫落，如果允許（航班）起飛，那么對飛機(jī)來說將是危險的。”
The forward - directed force developed in a jet or rocket engine as a reaction to the high - velocity rearward ejection of exhaust gases.
推力，側(cè)面壓力噴氣發(fā)動機(jī)或火箭發(fā)動機(jī)產(chǎn)生的作為高速向后排出的氣體的反作用力而向前推動的力量。
The rocket engine carries with it the oxygen of its own .
火箭發(fā)動機(jī)自帶氧氣。
Theory Of Operation: A rocket engine thrusts against a water filled syringe. This produces pressure readings on a connected pressure gauge.
理論的運作：一火箭發(fā)動機(jī)推力對一個充滿水的注射器，這產(chǎn)生的壓力讀數(shù)，就一連接壓力計。
The feed system of a rocket engine may be the cause of undesirable oscillations .
火箭供應(yīng)系統(tǒng)可能是有害的振源。
Rotor dynamic is one of the most complicated problems in development of LOX turbopump of liquid rocket engine.
轉(zhuǎn)子動力學(xué)問題是液體火箭發(fā)動機(jī)研制中最復(fù)雜的問題之一。
Another unconventional design element, the hybrid rocket engine that powers the suborbital vehicle, provides unique operational options.
另一個異于傳統(tǒng)的設(shè)計要素，是提供次軌道載具動力的混合式火箭引擎，它能提供獨特的操作選擇。
for liquid propellant rocket engine , it is an important condition for effective combustion that propellant be evaporated and mixed quickly.
在液體火箭發(fā)動機(jī)中，推進(jìn)劑組元迅速而高效的氣化和混和是產(chǎn)生高質(zhì)量燃燒所必須的重要條件。
The turbopump is an important part of the liquid rocket engine, whose task is fuel transporting.
渦輪泵是液體火箭發(fā)動機(jī)的重要組成部分，主要擔(dān)負(fù)燃料的輸送任務(wù)。
The mathematical models of the static characteristics of the full-flow staged combustion cycle rocket engine were presented.
建立了全流量補燃循環(huán)發(fā)動機(jī)的靜態(tài)特性的數(shù)學(xué)模型。
It is an important and basic issue to choose monitoring parameters of Liquid propellant Rocket Engine(LRE) monitoring system in ground test.
確定監(jiān)測參數(shù)是液體火箭發(fā)動機(jī)地面試驗監(jiān)控系統(tǒng)的一個重要而基礎(chǔ)的問題。
And, oil painter Robert McCall imagines the sight of the rocket engine firing to propel the lunar lander back to earth.
此外，油畫家羅伯特麥考想象的火箭發(fā)動機(jī)點火推動月球著陸器返“u200b”u200b回地球景象。
Russian teacher of that time, Konstantin Tsiolkovsky, decided that a rocket engine could provide power for a space vehicle.
康斯坦丁齊奧爾科夫斯基，俄羅斯老師，當(dāng)時的決定，可以為航天器提供電力的火箭發(fā)動機(jī)。
The detonation wave ignition technique is suitable to synchronization ignition of multi-chamber liquid rocket engine.
爆震波多管點火技術(shù)適合用于多燃燒室液體火箭發(fā)動機(jī)的同步點火。
For example, the rocket engine seal life just a few minutes, but require a short period of time does not leak.
例如，火箭發(fā)動機(jī)的密封壽命只需幾分鐘，但要求短時間內(nèi)絕對不漏。
Seen from above, the spacecraft Tycho Brahe is settled onto the HEAT-1X rocket engine.
從高空往下看，航天飛機(jī)第谷·布拉赫號正被安置到熱火-1X火箭發(fā)動機(jī)上。
A rocket engine typically goes faster but has to carry its own supply of oxygen.
火箭發(fā)動機(jī)通常使飛行更快，但需要自攜氧氣。
For one thing, they simplify the design of a rocket engine.
首先，它們可以簡化火箭發(fā)動機(jī)的設(shè)計。
The paper introduces a new method of measuring combustion time with CAT technique for solid rocket engine.
介紹一種應(yīng)用CAT技術(shù)確定固體火箭發(fā)動機(jī)燃燒時間的新方法。
Nonlinear regression algorithm based on quantum genetic algorithm was put forward to and applied in liquid rocket engine fault detection.
提出一種基于量子遺傳算法的非線性回歸算法，并應(yīng)用于液體火箭發(fā)動機(jī)故障檢測中。
It introduced the physical simulation model based on artificial neural networks on solid rocket engine milling process.
介紹了基于人工神經(jīng)網(wǎng)絡(luò)的固體火箭發(fā)動機(jī)藥柱銑削加工過程物理仿真模型。
How can a rocket engine that generates 5, 000 degree steam and 13, 800 pounds of thrust form icicles at the rim of its nozzle?
一個能制造出5000度高溫蒸汽和13800磅推力的火箭推進(jìn)器，是怎樣使噴口邊緣結(jié)冰的呢？
And rocket engine function test occupy the important status in the all kinds of tests of rocket.
而火箭發(fā)動機(jī)性能測試在火箭武器各類試驗中占有重要地位。
A rocket engine can work in space where there is no air.
火箭發(fā)動機(jī)能在沒有空氣的太空中工作。
Vortex Injection provides a form of swirl or cyclone combustion for a rocket engIne similar to systems often employed In Industrial furnaces
渦流噴射在火箭發(fā)動機(jī)中產(chǎn)生一種渦流或旋渦形式的燃燒，與工業(yè)爐中常采用的系統(tǒng)相似。
Implementation of A High Frequency Measuring System for the Testing of Combustion Instability Study of Tripropellant Rocket Engine
三組元發(fā)動機(jī)不穩(wěn)定燃燒研究試驗高頻采集系統(tǒng)的實現(xiàn)
Modeling and Dynamic Analysis of the Mass Flow Control System Used for Rocket Engine
用于火箭發(fā)動機(jī)的低溫流量控制系統(tǒng)建模及動態(tài)特性分析
Plume temperature measurement of a solid propellant rocket engine using multispectral thermometry
基于多光譜法的固體火箭發(fā)動機(jī)羽焰溫度測量
Application of immunity strategy for the study of the static characteristics of a rocket engine
免疫算法在火箭發(fā)動機(jī)靜態(tài)特性研究中的應(yīng)用
Principle and design of simulation test for acoustic characteristics of liquid rocket engine chamber with a single injector
液體火箭發(fā)動機(jī)單噴注器燃燒室聲學(xué)特性模擬實驗原理及實現(xiàn)
Numerical simulation of the temperature distribution in the turbo-pump system of a rocket engine during gliding
滑行過程中火箭發(fā)動機(jī)泵系統(tǒng)各構(gòu)件溫度數(shù)值模擬
The Design and Implementation of a Variable Thrust Liquid Propellant Rocket Engine Control System
一種大范圍變推力液體火箭發(fā)動機(jī)控制器的設(shè)計及實現(xiàn)
Numerical Simulation and Experimental Study of Viscous Flow Field in Rocket Engine propulsion
火箭發(fā)動機(jī)推力室粘性流場數(shù)值模擬及實驗
Fundamental study of fault monitoring and diagnostic technology of liquid rocket engine
液體發(fā)動機(jī)故障檢測與診斷中的基礎(chǔ)研究問題
A Comprehensive Numerical Model for Initial Propellant Temperature Effecting Liquid Rocket Engine Combustion Stability
推進(jìn)劑初始溫度影響液體火箭發(fā)動機(jī)燃燒穩(wěn)定性的數(shù)值模型
Kinematics Analyzed of a Virtual Axis Machine Tool Applied in Solid Rocket Engine Grain Machining
固體火箭發(fā)動機(jī)藥柱整形虛擬軸機(jī)床的運動學(xué)分析
