火箭噴流 的英文怎麼說

中文拼音 [huǒjiànpēnliú]
火箭噴流 英文
rocket discharge
  • 火 : fire
  • 箭 : 名詞（古代兵器） arrow
  • 噴 : 噴動詞1. （液體等受壓力而射出） spurt; spout; gush; jet 2. （噴灑） spray; sprinkle
  • 流 : Ⅰ動1 （液體移動; 流動） flow 2 （移動不定） drift; move; wander 3 （流傳; 傳播） spread 4 （向壞...
  • 火箭 : [航空] rocket; fire arrow; bird
  1. 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。
  2. 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。
  3. The 3 - d complex flowfield of rocket - missile with wings and empennages induced by the interaction between by base jet and the flow around the body has been numerically simulated. the main work is as follows : first, the gordon - mcbride program was developed to make it more friendly and efficient to the users

    本文對帶彈翼/尾翼彈箭的三維噴流繞流復雜流場進行了數值模擬，其主要研究內容有：首先，對gordon - mcbride火箭程序作了改進，使改進后的軟體具有了非常友好的人機交互界面。
  4. Then, the navier - stokes equations for 2 - d axisymmetric compressible turbulent flow were constructed and phoenics was used to simulate the 2 - d axisymmetric compressible turbulent flowfield of rocket jet

    其次，建立了二維軸對稱可壓縮湍流流動的平均navier - stokes方程，並利用phoenics軟體對二維軸對稱火箭噴流進行了數值模擬。
  5. The application of the jet impingement flowfield is wide, such as the vertical / short takeoff and landing ( v / stol ) aircraft, rocket, and the heat jet industrial application

    摘要噴射撞擊流在航空工程的應用有垂直短程起降飛機、火箭及熱噴射工業應用等。
  6. 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。
  7. Using swirl atomizer designed by this paper, kerosene was injected into the ejector combustor, and achieved steady combustion. this made a solid foundation for the future study on combustion organization

    設計了旋流式霧化噴嘴，實現了煤油在引射火箭模態中的穩定燃燒，為進一步的燃燒組織研究奠定了基礎。
  8. 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。
  9. 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。
  10. Two relevant models are intro - duced : ( 1 ) the neutrino rocket model for neutron stars with high velocities ; ( 2 ) the 3p2 - superfluid phase transi - tion model for pulsar glitches

    介紹了與之有關的兩個模型： （ 1 ）高速中子里的中微子火箭噴流模型； （ 2 ）脈沖星周期突變的3p2中子超流渦旋渦旋相振蕩模型。
  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 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。
  14. In addition, the usaf continues to fund development work of the aerojet ( formerly atlantic research ) variable flow ducted rocket ramjet system as a future propulsion option for an extended range aam

    此外，美國空軍繼續投資于航空噴氣研究所（原來的大西洋研究所）的可變噴流管火箭發動機系統，將其作為增程空空導彈的未來推進選項。
  15. Study on structural ageing reliability for flexible joint of solid rocket motor

    噴管擺動對固體火箭發動機內兩相流動的影響
  16. Lateral jet control technology is researched in this dissertation, based on supersonic / hypersonic missile aerodynamics and lateral jet interaction ( ji ) effects associated with the attitude control solid - propellant rocket motors system in the low endoatmospheric range

    橫向噴流干擾效應研究在超聲速高超聲速導彈總體設計和精確制導技術研究領域一直佔有重要地位。本論文針對大氣層內超聲速高超聲速導彈採用姿態固體火箭發動機側噴流控制技術的一些問題進行了研究。
  17. It is shown that when the exit area of secondary nozzle and the fuel / oxidizer ratio is fixed, the increase of mass flow rate of secondary flow lead to the decrease of velocity of mixed flow, and increase of total mass flow rate. the synthetical result of these two phenomenon cause the increase of thrust of rocket ejector, but the increasing magnitude is relatively small, indicating that these is no necessary to claim large bypass ratio in rocket ejector design. in the comparison between two configurations, the typical one has better performance, indicating the importance of pressure ratio

    結果表明：在固定二次噴管出口面積和氧燃比的條件下，二次流（引射空氣流）流量的增加引起混合氣體出口速度的下降和總流量的增加，二者綜合作用使發動機推力增加，但增幅不大，表明在設計發動機結構和工作參數時，不必過分追求大的引射系數；兩種結構的性能對比分析表明了增壓比對引射火箭性能的提高具有重要意義；對引射火箭的熱力循環分析同樣表明，增壓比對于提高發動機性能非常關鍵。
  18. 8 it looked like a shooting star at first, but then the track of light broadened into two things that looked like rocket exhausts and the thing came down without a sound

    一開始像是顆流星，可接著那軌跡越來越亮，變成兩個光點，就像是火箭噴出的氣流，那個東西一點沒出聲就著落了。
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