火箭發動機 的英文怎麼說
中文拼音 [huǒjiànfādòngjī]
火箭發動機
英文
engine; rocket-
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Unlike a rocket engine, the jet engine, as you know, is an " air breather "
正如你們所知道的，這種噴氣發動機與火箭發動機不同：它是「空氣噴氣發動機」 。As we all known, the ballistic trajectory is a pilotless missile, which loads rocket engine and control system, these will drop the missile to the target along its ballistic
眾所周知，彈道導彈是一種無人駕駛的飛行器，它裝有火箭發動機和控制系統，其目的是把導彈沿一定的彈道送到目標區。Bipropellant liquid rocket motor
二元推進劑液體火箭發動機Four nozzles, canted outboard, split the exhaust of the solid rocket motor into four equal tails.
四個向外傾斜的噴管把固體火箭發動機的排氣流分成四個相等的尾巴。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。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。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Study on boiling heat transfer enhancement of forced liquid nitrogen flow in lunate narrow channel
低溫液體火箭發動機循環預冷模擬試驗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。The liquids employed for rocket propulsion are called propergols.
用於火箭發動機的液體稱為液體火箭推進劑。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Vibration test method for solid rocket motors
固體火箭發動機振動試驗方法Web - based integrated design platform for solid rocket motor
的固體火箭發動機集成設計平臺Railway transportation test method for solid rocket motors
固體火箭發動機鐵路運輸試驗方法Shock test method for solid rocket motors
固體火箭發動機沖擊試驗方法分享友人