liquid rocket engine 中文意思是什麼

liquid rocket engine 解釋
液體火箭發動機
  • liquid : n 1 液體。2 【語言學】流音〈如 [l] [r]〉 adj 1 液體的，液態的，流動的。2 清澄的，透明的。3 易變的...
  • 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. 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
  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. 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。
  4. 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
  5. 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
  6. The dynamic thrust measure technology for high - altitude simulation test of the attitude control liquid rocket engine was studied in the thesis

    本文研究的是姿控發動機高空模擬試車中的動態推力測試技術問題。
  7. Rough set theory is a powerful tool in dealing with vague and uncertain information. in this paper, by analyzing the fault characteristics of liquid rocket engine and the rough set method, rough set theory was applied to mine the hot - firing test data of liquid rocket engine

    粗糙集是一種處理模糊和不確定知識的數學工具，在分析液體火箭發動機故障和粗糙集理論特點的基礎上，將粗糙集理論應用於液體火箭發動機試車數據挖掘中。
  8. By investigating 4 groups of test data of a certain type of engine, 24 original attributions were reduced to 2 groups, each group had 2 attributions, critical parameter combinations for fault diagnosis for liquid rocket engine were obtained ; 213 records were reduced to 5 or 6 records

    分析了某型號發動機的4組試車數據，將原來的24個屬性約簡為2組，每組有2個屬性，得到了在該樣本集中所有可能的、關鍵的、決定性的故障診斷因素的組合。針對每組，將原來的213個記錄分別約簡為5和6個。
  9. At last, the sensor fault diagnostic software of liquid rocket engine ground test system is developed successfully, including the designs of arithmetic, database and interface software

    本文開發了液體火箭發動機試車臺傳感器故障診斷系統，包括演算法實現、數據庫設計和用戶界面設計。
  10. Reliability assessment method in the case of zero - failure and few - failure data of liquid rocket engine is mainly researched in this dissertation, and it has carried on the discussion to the method that the reliability data conversion under different operating status

    本文主要研究了液體火箭發動機在無失效以及極少失效條件下的可靠性評估方法，並對不同工況下可靠性數據折算的方法進行了探討。
  11. The faults of liquid rocket engine are all kinds of abnormal states and the states different from preconcerted working states. the fault detection of liquid rocket engine is a judgement process for engine working state by measured data

    液體火箭發動機故障檢測是利用由傳感器測量得到的、反映發動機當前工作狀態的測量數據，經特徵提取后，對發動機是否正常工作做出可靠判斷的過程。
  12. In this paper, data mining was applied to acquire knowledge to solve the bottleneck problem of knowledge acquisition in the fault detection and diagnosis of liquid rocket engine

    本文利用數據挖掘技術提取知識，以克服液體火箭發動機故障檢測和診斷系統知識獲取的瓶頸。
  13. By applying the method to the hot - firing test data of liquid rocket engine in the starting - up and

    基於關聯規則的分類技術（ cars ）集成了關聯規則和分類這兩種挖掘技術，
  14. Moreover, the data processing method of accelerated life test is used to solve the problem of the reliability data conversion under different operating status to liquid rocket engine. and the counter power law model is introduced as the relation model between the characteristic life and the combustion chamber pressure, the accelerated life equation of the constant stress accelerated life test for the weibull distribution is obtained, through the accelerated life equation, the reliability estimate of different combustion chamber pressure is calculated

    再次，採用加速壽命試驗的數據處理方法對液體火箭發動機不同工況下可靠性數據折算的問題進行了研究，引入逆冪律模型作為特徵壽命與燃燒室壓力之間的關系模型，得到了weibull分佈下恆定應力加速試驗的加速壽命方程，並通過加速壽命方程折算出不同室壓下的可靠度估計。
  15. Safety rules for hoisting of liquid rocket engine

    液體火箭發動機吊裝安全規定
  16. The application of computer numerical modeling and simulation technology in liquid rocket engine spray combustion design is discussed. the suggestion for further development is presented

    討論了計算機數值模擬與模擬技術在液體火箭發動機噴霧燃燒設計中的應用並提出了進一步發展的意見。
  17. Abstract : the application of computer numerical modeling and simulation technology in liquid rocket engine spray combustion design is discussed. the suggestion for further development is presented

    文摘:討論了計算機數值模擬與模擬技術在液體火箭發動機噴霧燃燒設計中的應用並提出了進一步發展的意見。
  18. Liquid rocket engine is a thermal kinetic system, it runs under extremely strict physical conditions, such as high temperature, high pressure, strong erosion, high density of energy release, strong components parameters coupling. it is very difficult to establish accurate dynamic mathematical model

    液體火箭發動機是一種在極端的物理條件（如高溫、高壓、強腐蝕和高密度的能量釋放等）下運行的復雜的流體-熱動力系統，部件參數強烈耦合，很難建立精確的動態數學模型。
  19. 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。
  20. The fault diagnosis of liquid rocket engine can be considered as a problem of mode identification, the task of which is to divide samples into mode types by obtained characteristics

    液體火箭發動機故障診斷可視為一個模式識別問題，模式識別的任務是利用從樣本中提取出的特徵，將樣本劃分成相應的模式類別。
分享友人
分享到 Line

分享到臉書