火箭噴氣 的英文怎麼說

中文拼音 [huǒjiànpēnqì]
火箭噴氣 英文
rocket efflux
  • 火 : fire
  • 箭 : 名詞（古代兵器） arrow
  • 噴 : 噴動詞1. （液體等受壓力而射出） spurt; spout; gush; jet 2. （噴灑） spray; sprinkle
  • 氣 : Ⅰ名詞1 （氣體） gas 2 （空氣） air 3 （氣息） breath 4 （自然界冷熱陰晴等現象） weather 5 （氣味...
  • 火箭 : [航空] rocket; fire arrow; bird
  1. Unlike a rocket engine, the jet engine, as you know, is an " air breather "

    正如你們所知道的，這種噴氣發動機與火箭發動機不同：它是「空氣噴氣發動機」 。
  2. Four nozzles, canted outboard, split the exhaust of the solid rocket motor into four equal tails.

    四個向外傾斜的噴管把固體火箭發動機的排氣流分成四個相等的尾巴。
  3. In a short time interval, a mass dm of gas is ejected from the rocket.

    在很短的時間內，由火箭噴射氣體的質量為dm
  4. In this thesis, based on pershing ii surface to surface missile, a new kind of ballistic missile was designed with an additional rocket engine, which can be ignited twice. firstly, aerodynamic computational models of missile body and warhead which reentry with supersonic are built according to the task requirements ; secondly, the propulsion system model of missile is built whose first two stages are solid rocket engines and the third stage is liquid - solid combined rocket engine. the nozzle and the shape of the engine are designed to meet the needs of the populsion project ; thirdly, the trajectory model of the mass point is built and a wavy trajectory is designed & optimized ; finally, the ability of a missile ' s breaking through defence is analyzed

    以美國潘興導彈為原型，增加可兩次點火的末級發動機，改裝成具有跳躍能力的地地彈道導彈；首先，根據任務需求，建立了導彈的氣動模型，並建立了彈頭再入時高超聲速氣動模型；其次，建立了導彈推進系統模型，前兩級採用了固體火箭發動機，第三級採用了固?液組合火箭發動機，並在總體方案要求下，對發動機噴管和外形進行了設計；第三部分，建立了導彈質點彈道模型，設計了一條跳躍式彈道，並對跳躍式彈道進行了優化設計；最後，對導彈進行了突防能力分析，從分析的結果可以看出，跳躍式彈道的突防能力比常規的拋物線彈道要強。
  5. Starting with the invention of the bicycle, going on to sports cars, cars with jet engines, rocket - powered cars, attempts to break the sound barrier, and rocket - engine airplanes

    從發明自行車開始，一直到賽車，噴氣發動機汽車，火箭動力汽車，嘗試突破聲障和火箭動力飛機。
  6. The rockets give the planes and missiles enough speed to make the ramjet engine workable.

    這種助推火箭為飛機和導彈提供足夠的速度，以使沖壓式噴氣發動機可以開動工作。
  7. Israeli jets blast a palestinian militant group base outside the lebanese capital beirut, hours after rockets fired from lebanon hit a northern israeli border town

    以色列噴氣飛機襲擊一個駐扎在黎巴嫩首都貝魯特的巴勒斯坦武裝組織，火箭在黎巴嫩點驗幾小時后襲擊了以色列北部邊境的一個小鎮
  8. Unlike a rocket engine, the jet engine, as you know, is an "air breather".

    正如你們所知道的，這種噴氣發動機與火箭發動機不同：它是「空氣噴氣發動機」。
  9. An aircraft takeoff aided by an auxiliary jet or rocket

    助飛用噴氣機或火箭幫助航空器起飛
  10. The design of the rocket nozzle also has much to do with the behavior of the exhaust and the resulting velocity of the vehicle itself.

    火箭噴管的設計與排氣的性能及飛行器本身的有效速度也有很大關系。
  11. In this paper, simple reacting flow model in solid - propellant ducted rocket combustor based on eddy break - up model is established. the model is used to simulate the three - dimensional combustion flowfields in an experimental motor. some factors how to affect the combustion efficiency are discussed in the paper, including air intake and gas generator nozzle

    本文基於簡單反應的旋渦分裂模型，建立了固體火箭沖壓發動機補燃室內的湍流燃燒模型，並在該模型下對某實驗發動機進行了三維數值模擬，研究了補燃室設計參數包括進氣道出口設計參數和燃氣發生器噴管設計參數對燃燒效率的影響。
  12. By procceding from the all - gaseous state navier - stokes equation and using eno difference scheme, the limited cold - flow jets produced by ignitors are numerically simulated in srm chamber. then the flow field structure and characteristics are analyzed

    從曲線坐標下的完全氣體n - s方程出發，採用eno差分格式，對點火發動機工作初期，在固體火箭發動機內腔形成的受限冷噴流流場進行數值模擬;在此基礎上，分析了噴流的流場結構及特性。
  13. Abstract : by procceding from the all - gaseous state navier - stokes equation and using eno difference scheme, the limited cold - flow jets produced by ignitors are numerically simulated in srm chamber. then the flow field structure and characteristics are analyzed

    文摘:從曲線坐標下的完全氣體n - s方程出發，採用eno差分格式，對點火發動機工作初期，在固體火箭發動機內腔形成的受限冷噴流流場進行數值模擬;在此基礎上，分析了噴流的流場結構及特性。
  14. In addition, the usaf continues to fund development work of the aerojet ( formerly atlantic research ) variable flow ducted rocket ramjet system as a future propulsion option for an extended range aam

    此外，美國空軍繼續投資于航空噴氣研究所（原來的大西洋研究所）的可變噴流管火箭發動機系統，將其作為增程空空導彈的未來推進選項。
  15. Lateral jet control technology is researched in this dissertation, based on supersonic / hypersonic missile aerodynamics and lateral jet interaction ( ji ) effects associated with the attitude control solid - propellant rocket motors system in the low endoatmospheric range

    橫向噴流干擾效應研究在超聲速高超聲速導彈總體設計和精確制導技術研究領域一直佔有重要地位。本論文針對大氣層內超聲速高超聲速導彈採用姿態固體火箭發動機側噴流控制技術的一些問題進行了研究。
  16. It is shown that when the exit area of secondary nozzle and the fuel / oxidizer ratio is fixed, the increase of mass flow rate of secondary flow lead to the decrease of velocity of mixed flow, and increase of total mass flow rate. the synthetical result of these two phenomenon cause the increase of thrust of rocket ejector, but the increasing magnitude is relatively small, indicating that these is no necessary to claim large bypass ratio in rocket ejector design. in the comparison between two configurations, the typical one has better performance, indicating the importance of pressure ratio

    結果表明：在固定二次噴管出口面積和氧燃比的條件下，二次流（引射空氣流）流量的增加引起混合氣體出口速度的下降和總流量的增加，二者綜合作用使發動機推力增加，但增幅不大，表明在設計發動機結構和工作參數時，不必過分追求大的引射系數；兩種結構的性能對比分析表明了增壓比對引射火箭性能的提高具有重要意義；對引射火箭的熱力循環分析同樣表明，增壓比對于提高發動機性能非常關鍵。
  17. 8 it looked like a shooting star at first, but then the track of light broadened into two things that looked like rocket exhausts and the thing came down without a sound

    一開始像是顆流星，可接著那軌跡越來越亮，變成兩個光點，就像是火箭噴出的氣流，那個東西一點沒出聲就著落了。
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