箭形發動機 的英文怎麼說

中文拼音 [jiànxíngfādòngjī]
箭形發動機 英文
arrow engine
  • 箭 : 名詞（古代兵器） arrow
  • 發 : 名詞（頭發） hair
  • 機 : machineengine
  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. 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
  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. These offices, set up over the past 15 years, deploy artillery, rocket - launchers and aeroplanes to seed clouds with chemicals （ usually silver iodide ） that encourage droplets to form and fall where needed, or prevent the formation of destructive hailstones

    在過去的十五年中，這類辦公室相繼成立，它們調動大炮、火箭發射器和飛機，利用化學品（通常是碘化銀）來"播雲" ，作用要麼是促進雨滴形成后降到需要雨水的地方，要麼是防止破壞性冰雹形成。
  6. Interface debond between propellant and liner is a key form of failure of the structure integrity in the analysis of solid rocket motor

    在固體火箭發動機結構完整性分析中，襯層/推進劑藥柱粘接界面的脫粘是完整性被破壞的關鍵形式之一。
  7. It is determined now by calculation with mathematical relationship of the flight thrust to the physical quantities which can be measured directly. the optimization of the software development platform is also analyzed inspect of the solid rocket - ramjet developmental program

    其次，為滿足固體火箭沖壓發動機試驗技術進一步研究需要，在深入分析labview圖形化編程軟體優化方法的基礎上，改進了現有的固體火箭沖壓發動機試驗測控程序，並應用於發動機試驗中。
  8. New developments in decision theory, artificial theory and dynamic analysis method are applied to evaluation the possible projects. the main contents in this paper are included as follows : first, has improved an format reasoning method based on multiple attribute utility model and knowledgebase theory ; second, has proposed complex utility model by improving the theory of multiple attribute utility ; third, has presented a kind of weapon intelligent decision support system, based on the complex utility model and developed with com / dcom criterion ; forth, this paper also has build the dynamic simulation model for long - rang multiple tube rocket launcher system, and the tire dynamic model has applied in the rocket launcher system dynamic simulation model ; fifth, through building the rocket - launcher contact model, this paper has analyzed the dynamic forces between the rocket and launcher ; finally, this paper has build the evaluation model of the project about improving existing rocket launcher to the launcher that using canister, and get the conclusion through using the widss. the studies in this paper not only proposed scientific warrant to the choice of projects in this pre - studied national defense task about improving existing rocket launcher to the launcher that using canister, but also can give other studied tasks with decision supported

    主要內容包括：在總結決策分析與專家系統規則庫技術的基礎上，提出了融決策分析與專家系統規則庫技術於一體的形式化推理機制，該機制能有效的將定量計算和定性知識融為一體，將規范的決策分析解題過程與專家系統特有的演化推理方法有機結合起來；在多屬性效用理論的基礎上，建立了一般形式的復式效用模型，並實用化了全相關乘式效用模型，提供了較完善的通用建模、分析和解釋功能：引入了com dcom組件技術，開發了基於組件的widss系統，該系統基於形式化推理機制，易於擴展，能夠面向多種決策問題，具有較強的通用性；建立了遠程多管火箭炮全炮動力學模擬模型，將充氣輪胎動力學模型、輪胎和路面的相互作用模型運用於多管火箭炮動力學模擬計算中；利用碰撞接觸理論，對火箭彈在定向器管內的運動受力情況進行了模擬計算；建立了遠程多管火箭炮箱式發射改進方案模型，並利用動力學模擬計算結果在widss系統中進行了方案性能評估。
  9. 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
  10. This new method has the capability of calculating complicated 3d grain burning surface. dealing with evolving interface of complicated material and topology change ( splitting. breaking. merging ), based on level set method and burning surface process law. this technique can get accurate area of burning surface each moment and data of geometrical structure that provide access to examination of grain change in the srm working process. 2

    結合固體火箭發動機燃面推移規律，在等值面函數法基礎上開發的裝藥燃面演算法能夠成功計算任意復雜三維裝藥燃面，並且具有處理復雜物質邊界及其拓撲結構發生變化（如分裂、破碎、合併）的能力，能夠準確計算出發動機工作過程中各個時刻裝藥的燃燒面積，同時輸出裝藥幾何構形數據直觀地觀察裝藥的變化情況； 2
  11. 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。
  12. 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。
  13. The research work of this dissertation aims at the study of srm safety under mechanical impact. based on mechanism analysis of hotspots and by use of dynamic finite element method, efforts are focused on the establishment of a general theory applied for srm safety analysis under mechanical impact

    本文對機械撞擊載荷作用下固體火箭發動機安全性進行研究，以熱點機理分析為基礎，以結構動力有限元方法為手段，將熱點細觀模型與發動機結構撞擊變形分析有機結合，旨在探索機械撞擊載荷作用下固體火箭發動機安全性分析研究的方法和途徑。
  14. Then a new method is proposed to calculate the flanged connection system for rocket motors under the bolt - up and operating conditions

    然後考慮蠕變-鬆弛作用，提出了在預緊和操作情況下火箭發動機法蘭連接系統載荷與變形計算的新方法。
  15. 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。
  16. In this thesis the theory and method of intelligent fault diagnosis for a large turbo - pump fed liquid - propellant rocket engine ( lre ) is innovatively proposed and developed, based on the hybrid reasoning strategy and the hybrid knowledge models including mathematical model, logic model, graphic model and qualitative model. the theory and method are constructed in the way of intelligent modeling technique and creative application of knowledge engineering, and focus on the difficult problems and critical techniques such as the unified treatment of lre knowledge ( experience, facts, rules, graph, system structure, behavior, model knowledge and measured data ), the integration and translation of qualitative and quantitative knowledge, and the knowledge - based intelligent fault diagnosis reasoning methods. firstly, besides the correlation of different knowledge, the concept and the types of lre diagnosis knowledge are systematically described

    本文以某大型泵壓式液體火箭發動機為研究對象，以智能建模技術和知識工程的創造性應用為主要技術手段，圍繞著發動機知識（經驗、事實、規則、圖形、結構、行為、模型知識與測量數據信息等）的統一處理技術、定性定量知識的集成與轉化和基於知識的智能故障診斷推理等關鍵技術和難點，創新地研究發展了發動機基於混合知識模型（數學模型、邏輯模型、圖形模型及定性模型）和混合推理策略的智能故障診斷理論和方法。
  17. This software provides a user friendly, interactive, general tool and an integration environment for the design of srm metal case, which has overcome the deficiency of handwork and other methods. by use of this software, the whole design process, such as selecting the design scheme, confirming the performance, designing each part, calculating and analyzing the performance can be fulfilled. the whole design results can be saved as a single file, which is easily managed

    為固體火箭發動機金屬殼體設計提供了一個界面友好、交互性強、通用性好的設計工具與集成化的設計環境，用戶可以在該設計環境中完成設計方案的選擇、性能要求的確定、各部件的設計及最後的性能計算和分析等金屬殼體設計的整個流程，與以往的手工設計和其它設計方法相比，大大提高了設計的效率，而且整個設計結果以單個文件的形式保存，易於管理和查看。
  18. Collaborative optimization method is studied in depth, the causes leading to computational difficulty of this method are discussed by optimization theory and computation examples, and improve method which may solve this problem is presented. based on the comparison of several optimization methods and the characteristics of modern rocket - ramjet, step optimization pattern - a new integrated design mode is presented and is used to realize integrated design of rocket - ramjet. inner and outer fiowfield of a certain integral rocket - ramjet missile is simulated numerically using n - s equation

    （ 2 ）系統地研究了導彈總體優化設計方法，探討了多學科設計優化的原理、框架結構、具體表述形式，深入研究了協作優化方法的原理，從優化原理和算例兩方面討論了造成協作優化方法計算困難的原因，提出了可能克服這種計算困難的改進途徑；在比較幾種優化方法的基礎上，針對新一代沖壓式導彈的特點，提出了一體化設計的模式? ?分步優化模式，進行了整體式火箭沖壓發動機反艦導彈總體參數的一體化設計。
  19. Involving interaction of gasket, bolts and flange rings, the load - deformation and the structural fuzzy reliability of each component are analyzed in the case of ideality, external loads and creep - relaxation respectively. and then, the sealing fuzzy reliability of the flanged connection system is researched. the function of each part of genetic algorithm is analyzed in application to nonlinear unconstrained and constrained optimization

    本文將墊片、螺栓和法蘭作為一個相互作用的整體，比較深入地分析了理想情況下、有外載作用及蠕變-鬆弛影響下，平墊片和0形圈這兩種典型的火箭發動機法蘭連接系統各元件的載荷與變形、元件的結構可靠度和火箭發動機法蘭系統的密封可靠度。
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