火箭燃燒系統 的英文怎麼說

中文拼音 [huǒjiànránshāoxìtǒng]
火箭燃燒系統 英文
rocket combustion system
  • 火 : fire
  • 箭 : 名詞（古代兵器） arrow
  • 燃 : 動詞1. （燃燒） burn 2. （引火點著） ignite; light
  • 燒 : Ⅰ動詞1 （使東西著火） burn 2 （加熱或接觸某些化學藥品、放射性物質等使物體起變化） cook; bake; hea...
  • 系 : 系動詞（打結; 扣） tie; fasten; do up; button up
  • 統 : Ⅰ名詞1 （事物間連續的關系） interconnected system 2 （衣服等的筒狀部分） any tube shaped part of ...
  • 火箭 : [航空] rocket; fire arrow; bird
  • 燃燒 : （物質劇烈氧化而發光、發熱; 燒） burn; kindle; flame; set on fire; [化學] combustion; inflammation; ignition
  • 系統 : 1. （按一定關系組成的同類事物） system 2. （有條理的;有系統的） systematic
  1. 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。
  2. 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
  3. It has a large region of application in solid rocket motor grain design and has made new improvements compared with other available codes. user can easily and rapidly build his initial grain shapes and then obtain geometric information of his design. according to the theory describeds in the paper, the regressions of the burning surface area and the pressure are obtainded

    該系統擴展了固體火箭發動機裝藥的設計能力，用戶可利用它簡捷地構造出三維藥柱的初始形狀，並獲得設計所需的各個幾何參數，進而依據本論文提出的復雜三維藥柱內腔燃燒推移和燃面計算的方法，計算出燃面變化和壓強變化，得到推力隨時間變化的曲線，再依據這些計算結果進行再設計，直至達到滿意的結果為止。
  4. This paper describes a new computer program ( regresssd ) to simulate the regression of complex 3 _ d grain cavity and calculate the burning surface area

    本論文介紹了一種新的固體火箭發動機復雜三維藥柱內腔燃燒推移和燃面計算的動態模擬和計算系統。
  5. It helps to know the status of program running and program communication. it gives intuitive references to find out performance bottlenecks and advices to optimize programs. to validate the applicability and validity of the system, the parallel program performance of combustion processes of liquid rocket engine is monitored and analyzed by using the analysis system

    為了驗證系統的實用性和有效性，運用該分析系統在機群上對液體火箭燃燒過程模擬程序進行了監測與性能分析，預測了程序的執行和通信時間，定位了該程序的性能瓶頸，給出了優化建議。
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