火箭設計 的英文怎麼說

中文拼音 [huǒjiànshèjì]
火箭設計 英文
rocket design
  • 火 : fire
  • 箭 : 名詞（古代兵器） arrow
  • 設 : Ⅰ動詞1 （設立; 布置） set up; establish; found 2 （籌劃） work out : 設計陷害 plot a frame up; fr...
  • 計 : Ⅰ動詞1 （計算） count; compute; calculate; number 2 （設想; 打算） plan; plot Ⅱ名詞1 （測量或計算...
  • 火箭 : [航空] rocket; fire arrow; bird
  • 設計 : devise; project; plan; design; excogitation; layout; layout work; styling
  1. At the same time, we colligated general math models and solving methods of reliability which are on using now. all of the models and methods have been compared and analysed

    結構可靠性設計是固體火箭發動機研究工作中的重要內容。採用可靠性設計方法，可以確保發動機實現預定的質量指標。
  2. Design method for aft - end igniter of small - scale solid rocket motor

    小型固體火箭發動機尾部點火器設計方法
  3. Lm - 2f chief designer talk about quality control

    神舟六號發射后采訪火箭系統總設計師劉竹生
  4. 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
  5. Design optimization for solid rocket motor based on graph morphing

    基於圖形變形法的固體火箭發動機優化設計
  6. Study on parallelism measurement technique of multibarrel launcher

    多管火箭炮平行性測量系統設計
  7. 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。
  8. Abstract : solid propellant rocket motors are preferred for most ballistic missiles because they need simple maintenance and can be launched quickly. but the conventional thrust termination devices limit the depletion of every stage ' s grain and increase some extra - weight. an improved method for designing a multi - stage solid rocket based depleted shutdown was provided. in order to solve the problem of lack of thrust termination devices, a device to adjust the burnout angle will match the final burnout velocity and satisfy the desired range. the method can also limit the detection from anti - ballistic missile system

    文摘:由於維護簡單和發射快速，彈道導彈多用固體火箭發動機，但繁雜的推力終止裝置使各級裝藥不能耗盡並讓結構增重.提出了一種對基於耗盡關機多級固體火箭概念設計的改進方法，此方法滿足導彈系統主要的戰技要求.為解決無推力終止裝置的末速不準問題，可在末級發動機採用姿態調整裝置，對射角進行調整，配合末速以滿足射程要求.本方法還可抑制敵方反導探測
  9. Design of the multiple rocket launcher loading training simulator based on vr

    的火箭炮裝填訓練模擬器的設計
  10. Web - based integrated design platform for solid rocket motor

    的固體火箭發動機集成設計平臺
  11. Uncertainty optimization design of solid rocket motor grain

    固體火箭發動機裝藥不確定性優化設計
  12. This course contains labs, assignments, projects, and related resources dealing with aircraft and rocketry design concepts

    本課程包括實驗、作業、項目設計和關于航天器和火箭設計概念的相關資料。
  13. Building on design work that began in 1996, scaled composites began developing a launch aircraft called the white knight, a three - seat rocket plane known as spaceshipone and associated ground operations [ see illustrations on pages 92 to 94 ]

    縮尺復合公司以1996年開始進行的設計為基礎，發展一架發射飛機白騎士、一架三人座火箭飛機太空船一號，和相關的地面操作系統（見88 ~ 90頁圖） 。
  14. 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。
  15. This paper relies on country 863 project " taking off levelly, two stage to orbit and transatmosphere flight vehicle system design ", research towed flight dynamics primarily, development for our country air launch technology of carrier rocket, offering the essential technological reserve

    本論文以國家863項目「水平起飛兩級入軌跨大氣層飛行器總體設計」為依託，對牽引飛行動力學進行初步研究，為我國研究運載火箭空中發射技術提供必要的技術儲備。
  16. It can be used not only to change the fire precision of the base bleed projectile, but also to improve the effect of reduction drag and expansion range. the calculating model of the secondary expansive pressure of the burning gas is constructed by means of analysis of the experimental resuits, it has been confirmed that the new base bleed unit can be designed, with the secondary expansive principle of the burning gas pressure. the engineering project of a hybrid base - bleed - rocket high - level efficient extended - range projectile is designed, with the secondary expansive principle of the burning gas pressure, the feasibility and the true worth of its engineering applications is validated in theory

    本文提出了底排燃氣壓力不隨外部壓力變化，既可改善底部彈射擊精度又可提高減阻效果的二次擴張原理，建立了底排燃氣二次擴張壓力的計算模型，並通過採用二次擴張原理的新型底排裝置與傳統底排裝置的對比試驗，驗證了新型底排裝置結構實現的可行性；完成了基於底排燃氣二次擴張高效增程原理的底排?火箭復合高效增程彈方案設計及其有關計算，從理論上驗證了其工程應用的可行性和實際價值。
  17. 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
  18. The conclusion that the optimal secondary nozzle exit area generating the maximum thrust agrees well with the numerical simulation, indicating that the exit area of secondary nozzle should be optimized according to structure and flow parameters during design

    表明在引射火箭設計時，應結合引射火箭的結構和流動參數對二次噴管出口面積進行優化設計，以達到最佳推力性能。
  19. Most of the work that has gone into the design of rockets has centered on missile (weapon) development.

    涉及火箭設計的大部分工作已經以研製導彈（武器）為中心了。
  20. Arde aircraft and rocket design engineers

    飛機與火箭設計工程師
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