rocket engine 中文意思是什麼

rocket engine 解釋
火箭發動機
  • rocket : n 火箭；火箭彈，火箭發動機；火箭式投射器；〈英俚〉斥責。 a carrier [freight] rocket 載運火箭。 an...
  • engine : n. 1. 機械，機器。2. 引擎，蒸汽機，發動機。3. 機車，車頭。4. 工具；〈古語〉方法，手段。vt. 給…安裝發動機。
  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. As we all known, the ballistic trajectory is a pilotless missile, which loads rocket engine and control system, these will drop the missile to the target along its ballistic

    眾所周知，彈道導彈是一種無人駕駛的飛行器，它裝有火箭發動機和控制系統，其目的是把導彈沿一定的彈道送到目標區。
  3. Vortex injection provides a form of swirl or cyclone combustion for a rocket engine similar to systems often employed in industrial furnaces.

    渦流噴射在火箭發動機中產生一種渦流或旋渦形式的燃燒，與工業爐中常採用的系統相似。
  4. The feed system of a rocket engine may be the cause of undesirable oscillations.

    火箭供應系統可能是有害的振源。
  5. Abstract : the development of lox lh2 rocket engine in the world is reviewed, and the current situation and differences of the engines in china are analysed

    文摘:回顧了各國氫氧發動機的發展概況，對我國的現狀和差距作了比較。
  6. Technology of loxodrome coolant channel machining on liquid rocket engine. yuhang xuebao / journal of astronautics. vol. 24 no. 3. may, 2003. wang yongqing ， lu jiechi, tong yu

    等傾角螺旋槽的片銑刀銑削加工技術.工具技術. 2002年第8期. 2002年8月.王永青，盧傑持
  7. Disigning coolant channel on the firebox of liquid rocket engine to loxodrome ( equal - angle helix ) groove can improve firebox coolant capability greatly. because the width dimension of loxodrome groove is narrow and the depth is deep, some machining methods are incapable, such as end - milling or electrochemistry. according to the peculiarities, a cnc disk - cutter - milling method which is composed of five motion axes with four simultaneously interpolated ones is researched. because most firebox generatrix is composed of complex curves, it is very difficult to get cnc cutting program with manual means. in order to deal with the problem, the loxodrome mathematics model is studied, and an auto - programming software system is developed. the software system can generate cnc cutting program of loxodrome on many kinds of turned surface. the constriction - distension segment of firebox is the most representative workpiece. the sharp changing of its generatrix slope makes loxodrome milling difficult. with the theory analyzing and practice cutting experiment, some applied techniques, which include milling mode and direction, choosing cutter diameter and cutting start point setting, are developed. adopting the technology above, tens regular workpiece have been manufacturing. the two - year manufacture practice has confirmed the validity and feasibility of developed loxodrome coolant channel milling method. the developed technology is also worth to be referenced to other similar workpiece

    將液體火箭發動機燃燒室的冷卻通道設計為斜航線（等傾角螺旋線）槽形，可以大幅度改善燃燒室的冷卻性能.斜航線冷卻槽的槽寬尺寸較小而槽深尺寸較大，所以無法使用棒銑刀銑削、電化學等加工方式.針對這些特點，提出了五軸控制、四軸聯動的數控片銑刀銑削加工方法.由於燃燒室外表面的母線輪廓復雜，手工編制數控加工程序難度大.為了解決數控加工程序的編制問題，研究了斜航線的數學模型，開發了自動編程軟體系統.使用該系統，可以生成多種母線輪廓回轉體外表面上的斜航線數控加工程序.燃燒室收斂-擴張段的母線斜率變化大，加工難度大，是斜航線冷卻通道加工的最典型工件.經過理論分析和實際切削實驗，研究了針對該類型工件的片銑刀直徑選擇、銑削方式和方向、刀具調整和起刀點的設置等多項實際的加工方案.採用上述的一系列技術，已經成功地加工了數十個合格工件.經過兩年多的實際生產過程應用，驗證了所開發的斜航線冷卻通道加工方法的正確性和可行性.這些加工技術的研製成功，對其他相似類型零件的加工亦具有參考意義
  8. 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。
  9. For one thing, they simplify the design of a rocket engine.

    首先，它們可以簡化火箭發動機的設計。
  10. 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。
  11. On the part of the theory of the automatic test technology used in the rocket engine ground test, on the basis of the architectures and standards of some typical automatic test systems ( ats ), the test action model, ats data model, database model and the universal instrument - driving model are established

    在火箭發動機地面試驗自動測試技術理論方面，在典型自動測試系統（ ats ）的體系結構和相關標準的基礎上，建立了火箭發動機地面試驗測試行為模型、 ats數據模型、數據庫模型和通用儀器驅動模型，然後，建立了面向火箭發動機地面試驗的開放式柔性ats體系結構軟硬體模型。
  12. Aiming at the conveying - alcohol pipe system of a certin model gas generator in our school rocket engine field laboratory, this paper does a series of simulation studies using amesim, analyses and summarizes the results of simulations, and at the same time implements some waterhammer experiments, and compares the results with the ones of simulations

    本文針對我校火箭發動機試驗外場的某型燃發器試驗酒精供應管道系統，使用amesim進行了一系列的模擬研究，對模擬的結果進行了分析和總結，同時還開展了水擊試驗，並與模擬進行了對比。
  13. Analysis of failure and optimization for composite case of solid rocket engine

    固體火箭發動機復合材料殼體破壞分析及優化
  14. Transient characteristics during pulse operation of liquid feed line for the attitude control rocket engine

    姿控發動機脈沖工作的管路瞬變特性
  15. Abstract : this paper introduces the principles of doppler radar signal processing method in the modulation. it provides the processing method for projectile tracer time, the burst time, rocket engine working time, projectile spin and flight attitude from signal of doppler radar

    文摘:介紹了測速雷達調制域彈道信息處理方法的工作原理，詳細論述了從測速雷達信號中處理彈丸曳光時間、底排燃燒工作時間、火箭發動機工作時間、彈丸旋轉速度、飛行姿態角和擺動周期等彈道信息的方法。
  16. Both advantages of rocket engine and air - breathing engine are integrated into one kind of propulsion system, called rocket - based - combined - cycle ( rbcc ), which has multiple operating woke modes, including ejecting, subsonic combustion, supersonic combustion and rocket mode, with each mode operating at varying flying stage. rbcc has prominent potential of high efficiency and low cost, and so it is recognized as an advanced propulsion system of future single - stage - to - orbit reusable spacecraft and hipper - sonic missile. it has been broadly investigated in foreign countries and has been progressed into small and full - scale flying stage

    火箭基組合動力循環（ rbcc ， rocketbasedcombinedcycle ）將傳統的火箭發動機和吸氣式發動機的優點集中組合到一個具有多種工作模態（包括引射、亞燃、超燃及火箭模態）的發動機里，在不同的飛行階段啟用不同的工作模態，因此具有大幅提高航天推進系統經濟性與高效性的潛在優勢，並可能發展成為下一代單級可重復使用航天器以及高超聲速導彈武器的動力系統。
  17. 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」。
  18. Propositional logic - based method of liquid rocket engine fault diagnosis

    液體火箭發動機故障診斷的命題邏輯方法
  19. Although that effort did not succeed, it led to the development of several critical technologies, in particular a rocket engine

    雖然那個計畫沒有成功，幾項關鍵技術卻都發展出來了，包括火箭引擎。
  20. Finite element analysis based on ansys of ball - socket nozzle ' s pendulous socket in solid - rocket engine

    的固體火箭發動機珠承噴管擺動接頭的有限元分析
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