燃燒箭 的英文怎麼說

中文拼音 [ránshāojiàn]
燃燒箭 英文
flaming arrows
  • 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...
  • 箭 : 名詞（古代兵器） arrow
  • 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
  1. T crowe, et al. effect of spin on the internal ballistics of a solid - propellant motor r. aiaa 66 523

    曹泰岳，常顯奇，等.固體火箭發動機燃燒過程理論基礎m .長沙：國防科技大學出版社
  2. C t crowe, et al. effect of spin on the internal ballistics of a solid - propellant motor r. aiaa 66 523

    曹泰岳，常顯奇，等.固體火箭發動機燃燒過程理論基礎m .長沙：國防科技大學出版社
  3. D r greatrix. acceleration - base combustion augmentation modelling for non - cylindrical grain solid rocket motors r. aiaa 95 2876

    曹泰岳，常顯奇，等.固體火箭發動機燃燒過程理論基礎m .長沙：國防科技大學出版社
  4. Mayer a e h j, stowe r a. experimental study into mixing in a solid fuel ducted rocket combustion chamber [ r ]. aiaa 2000 - 3346

    餘勇，陳小前，等.三維實驗固體火箭沖壓發動機燃燒室湍流反應流數值模擬[ j ] .國防科技大學學報， 2002 ， （ 5 ）
  5. 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。
  6. 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
  7. Kjv ： he hath also prepared for him the instruments of death ; he ordaineth his arrows against the persecutors

    新譯本：他親自預備了致命的武器，他使所射的箭成為燃燒的箭。
  8. Calculation of nozzle efficiency for solid rocket motor

    固體火箭發動機燃燒室噴管一體化網格生成
  9. To appreciate the unsteady environment existing in liquid propellant rocket chambers it is necessary that the steady state be well understood.

    為了分析液體推進劑火箭發動機燃燒室中存在的非穩態環境，必須很好地了解穩態狀態。
  10. This was a night when rafer alston had 18 points and 10 assists, when luther head had 22 points and was actually seen attacking the basket, when bonzi wells came off the bench to deliver 17 and 8 boards, when shane battier struggled through a horrid start and made three critical 3 - pointers to keep fanning the flames alive

    這一夜，阿爾斯通18分10助攻；海德狂砍22分，攻籃很成功；威爾斯替補上場，搶17分8板，巴蒂爾開場表現稀爛，但關鍵時刻貢獻了3個3分，讓火箭的進攻火焰燃燒得更猛。
  11. Design optimization of chamber pressure and nozzle area expansion ratio of solid rocket motors

    固體火箭發動機燃燒室壓強及噴管擴張比優化設計
  12. Because the propellant grain is viscoelastic material, the liner and adiabatic layer are also viscoelastic one, the interface debond problem is actually interface crack about elastic - viscoelastic or bi - viscoelastic materials. research about this problem relates to the knowledge of viscoelastic mechanics and interface fracture and combustion. numerical analysis method about interface debond on solid rocket motor is researched in this paper

    由於固體火箭發動機的推進劑藥柱是一種粘彈性材料，襯層和絕熱層也具有粘彈性性質，因此其界面脫粘問題實際上是彈性-粘彈性或雙粘彈性各向同性材料界面裂紋問題，對該問題的研究涉及到粘彈性力學、界面斷裂力學和燃燒學等相關學科。
  13. 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。
  14. During its storage, transportation, maintenance and service, the solid rocket motor ( srm ) may encounter many incidents such as being dropped onto the ground while being hoisted up, crashing when vehicle turns over during transportation, being struck heavily in takeoff or landing accident while being carried by airplane, impacting with launch platform or buildings when there is abnormality during launch of multiple - stage rocket. impact of great intensity takes place in such accidents, which will lead to srm ignition or explosion

    固體火箭發動機在貯存、運輸、維護及使用過程中可能遇到各種意外機械撞擊激勵，例如:吊裝過程中跌落，運輸過程中因交通事故發生翻覆碰撞，機載固體導彈掛飛時因載機發生起降事故導致高速沖撞，多級火箭發射初期因發射異常與發射架或地面建築物發生碰撞等，固體火箭發動機將受到劇烈機械撞擊載荷作用，導致其著火燃燒甚至爆炸。
  15. Through malfunction of the tests of 810 research institute, the combustion performance of the hybrid motor and model about regression rate have been studied in the dissertation. the main aspects are as follows : the performance of the hno3 + n2o4 - htpb hybrid rocket motor were all discussed

    本文結合航天科技集團公司810研究所正在研製的ak - 20l / htpb + al組合固液火箭發動機，開展了固液火箭發動機混合燃燒特性的數值模擬工作，在此基礎上給出固體燃料退移速率預示模型及預示結果。
  16. The effect of area ratio, mach number, total pressure of primary rocket and geometry structure of primary rocket on ejectorjet performance was studied

    通過數值計算研究了引射火箭堵塞比、來流馬赫數、一次火箭燃燒室總壓、一次火箭構型對引射火箭性能的影響。
  17. The burning surface of the powder then increases, the pressure rises and the rocket may be blown up.

    此時，無煙藥燃燒表面增加，壓力上升，火箭可能爆炸。
  18. 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。
  19. To study the acoustic unsteady combustion of srm, built the acoustic model of chamber. deduced the little amplitude sound wave 3d equation, used the finite volume discrete method to simulate. got the vibration model of three kinds of chamber

    為研究固體火箭發動機聲不穩定燃燒特性，建立了燃燒室內聲學特性分析的物理數學模型，推導了小振幅聲波三維波動方程，採用有限體積離散方法進行模擬，得到圓柱型、四片翼柱彤和五片翼柱型藥柱三種燃燒室形狀聲學振動基本模態
  20. Using swirl atomizer designed by this paper, kerosene was injected into the ejector combustor, and achieved steady combustion. this made a solid foundation for the future study on combustion organization

    設計了旋流式霧化噴嘴，實現了煤油在引射火箭模態中的穩定燃燒，為進一步的燃燒組織研究奠定了基礎。
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