火箭燃燒室 的英文怎麼說
中文拼音 [huǒjiànránshāoshì]
火箭燃燒室
英文
rocket chamber-
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 ）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。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。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。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Submerged nozzles are commonly preferred in large solid rocket motors. the aft - end internal flows are very complex because of submergence. the flow process and mechanism are not very clear yet
大型的固體火箭發動機通常採用潛入式噴管，其燃燒室尾部的流動非常復雜，流動過程及其機理尚不十分清楚。The experimental results indicates that the secondary mass flow increases with increasing of primary mass flow rate, but the bypass decrease because the primary mass flow rate increase more rapidly than secondary mass flow. the expansion configuration shows low thrust property due to low pressure in flow path. the secondary nozzle changes the pressure distribution in ejector combustor, and decreases bypass ratio, but obtain more completely mixing
結果表明：二次流流量隨著一次流流量的增加而增加，由於二次流流量的增加速度低於一次流，引射系數減小；在純擴張式結構實驗中，引射燃燒室壓強很低，難以實驗推力增強；二次噴管改變了引射燃燒室的壓強分佈，降低了引射系數，改善了混合狀況能；對于本文的實驗結構，存在一個最優的二次噴管出口面積，使引射火箭推力最大，同數值模擬結果相吻合。Engineering drawing system can draw two dimension curve graphs, main detail drawing and assembly drawing. the curve of internal trajectory and dynamic simulation of particle external trajectory. the detail drawing includes the graph of chamber, grain design, connection body, nozzle, some standard part
工程繪圖可以繪制二維曲線圖和零部件圖，其中二維曲線包括有內彈道壓（推）力?時間曲線、質點外彈道動態模擬曲線；零部件圖包括有標準螺栓與螺紋孔、燃燒室結構圖、裝藥設計截面圖、連接底結構圖、噴管結構圖及火箭發動機總體裝配圖。In the thesis, the combustions ( ejector ' s first combustion and ramjet ' s secondary combustion ) organization of a typical structure of rbcc jet ? strutjet, was studied and analyzed, to get a better and dynamic method, to organize such kind of combustions
論文從rbcc發動機的一種典型結構- - - -支板引射火箭發動機（ strutjet ）出發，分析了這種組合發動機的燃燒（引射火箭的一次燃燒與沖壓補燃室中的二次燃燒）組織，獲得了組織這類燃燒的較好方法?實時、動態的智能組織。The effect of secondary fuel nozzle location, the mass flow rate of secondary fuel and outlet area of ejectorjet were studied. the main results are : the geometry structure of ejectorjet can be compatible with other rbcc operation modes by secondary combustion organization ; the distribution of secondary fuel on ejectorjet cross section is significant for secondary combustion stability. spi combustion organization method is promising
實驗研究了二次燃料噴注位置、二次燃料噴注量、后體出口面積對引射火箭性能的影響，得到的結論為：通過燃燒組織，引射火箭模態可以和其他工作模態（亞燃超燃）共用燃燒室而不需做大的幾何變化；二次燃料在引射火箭通道截面上的分佈對于引射火箭的穩定工作有重要意義。With computations and analysis, the comprehension on the mixing and combustion process is increased, and some significative results are listed below : a ) there are three recirculation regions and one vortex region in the combustor, and these recirculation regions affect the combustion process deeply, b ) increasing side - arm angle and moving side - air inlet position toward the fuel inlet can improve mixing and combustion characteristics, and increase the combustion efficiency, c ) when the angle between two air - inlets equals to 180
通過計算與分析，增進了對補燃室內摻混燃燒過程的理解，為固體火箭沖壓發動機補燃室設計提供了一些有意義的結果： 1補燃室內的流動十分復雜，存在三個迴流區和一個旋渦區，迴流區對摻混燃燒過程有重要影響； 2增大空氣入射角度、向前移動進氣道出口位置有利於增強頭部迴流區強度，增強摻混效果，燃燒效率上升； 3Coupling computation on radial vibration of chamber structure and internal ballistic property for solid rocket motor
固體火箭發動機燃燒室結構徑向振動與內彈道性能的耦合計算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。Abstract : the review presents the recent status and achievements on numerical simulation studies of solid rocket motor chamber internal flow field from three aspects, including numerical analysis of internal flow during the ignition transient period, fin - slot flows in solid rocket motor, and calculation of particle trajectories and slag deposition. it also puts forward the focal points of research on numerical simulation of solid rocket motor chamber internal flow field in our country
文摘:從三個方面介紹了固體火箭發動機燃燒室內流場數值模擬研究的現狀及取得的成果，包括發動機點火傳播及起動過程的數值研究，翼環槽內流場研究和粒子軌跡、熔渣計算，並對我國開展此項研究的重點提出了建議。分享友人