進氣道模型 的英文怎麼說

中文拼音 [jìnqìdàomóxíng]
進氣道模型 英文
model air intake
  • 進 : 進構詞成分。
  • 氣 : Ⅰ名詞1 （氣體） gas 2 （空氣） air 3 （氣息） breath 4 （自然界冷熱陰晴等現象） weather 5 （氣味...
  • 道 : Ⅰ名詞（道路） road; way; route; path 2 （水流通過的途徑） channel; course 3 （方向; 方法; 道理） ...
  • 模 : 模名詞1. （模子） mould; pattern; matrix 2. （姓氏） a surname
  • 氣道 : air flue; air passage
  • 模型 : 1 （仿製實物） model; pattern 2 （制砂型的工具） mould; pattern3 （模子） model set; mould patter...
  1. 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。
  2. On the basis of these results, the relations of total - pressure recovery coefficient or flow coefficient and flight mach number, angle of attack and the second movable wedge angle of the inlet have been founded by hypersurface fitting, then the mathematical model of the inlet is established

    根據流場計算結果並利用超曲面擬合方法建立了進氣道總壓恢復系數、流量系數與飛行馬赫數、進氣道攻角及二級可調斜板角度之間的關系，由此得到了二元混壓式超聲速進氣道數學模型。
  3. Computational fluid dynamics ( cfd ) techniques are used to study and understand fluid behavior in tunnels. by simulating complex specific operational cases, we can educe velocity or flux distribution in tunnel under different ventilation and resistance situation and determine the favorable operational procedures of the erlang mountain tunnel ventilation in a fire case. comparison has been made between a simulation and experiment for some cases in order to prove the cfd model is powerful, so that enables the study of cases for which experimental data is not available

    採用本文將隧道內的氣流看成是理想流體的一維恆定流動，通過對二郎山特長公路隧道半橫向通風系統建立隧道內的空氣動力學模型，利用計算機進行數值分析與計算，得出發生火災時，不同通風阻力條件下隧道中的風速分佈及流量分佈，並通過實驗室隧道模型實驗進行驗證與修正，依據研究結果給出了二郎山半橫向通風隧道的火災控制方案，從而解決了二郎山公路隧道通風對火災的控制問題，同時為半橫向通風公路隧道的火災通風提供科學的方法。
  4. The analysis of results is also valuable for designing, researching and operating of other semi - transient ventilating road vehicle tunnel

    5軟體對隧道內氣流流動情況進行計算機模擬與分析，並搭建了二郎山隧道模型，進行實驗研究。
  5. Use commercial software numeca to calculate the flow - field of the inlet of the lsc with an insert - board, and analyze the flow - field. also a piv ( particle image velocimetry ) flow - field testing scheme is designed, but have not been carried out for some reasons, for reference only

    同時還利用numeca商業軟體對以這臺壓氣機為模型的進氣道在插板作用下的流場計算及分析，另外還設計了piv流場測量方案，因為種種原因沒有能夠最終進行試驗，僅供參考。
  6. A parametric analysis of the inviscid effects of leading edge sweep, sidewall compression, width - height ratio, cowl position and inflow mach number on spillage is finished. numerical simulations are completed for a series of inlets at various flight height and velocity. the research indicates that the area of spillage window, which is mainly determined by the position of the cowl, significantly influences the spillage characteristic of the scramjet inlet

    闡明了側板后掠的側壓進氣道設計參數對構型溢流影響;對不同側板配置方式的側壓式進氣道進行了數值模擬，通過對比分析，發現由唇口板的位置所決定的溢流窗面積的大小對進氣道溢流特性的影響顯著。
  7. 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。
  8. The fuel diffusion and vaporization model in the intake port of small gasoline engine are analyzed, and the key factors affecting the formation of droplet and film are generalized

    本文對小型汽油機進氣道內燃油霧化和蒸發模型進行了分析，總結出了影響油滴油膜形成和蒸發的主要因素。
  9. The full flow field characteristics of a supersonic inlet are illustrated at design conditions ; the influence of attack angle on flow field of the inlet is investigated ; b - spline theory is used to model the inlet with attack angle

    給出了設計狀態下進氣道內外流場特徵；分析了攻角變化對進氣道流場的影響；以數值模擬結果為基礎，利用b樣條理論建立了反映攻角、馬赫數及可調斜板角度變化的超聲速進氣道數學模型。
  10. 2. after the appropriate mathematical and physical model was proposed, the numerical calculation was processed in fluent

    2 .根據進氣道內的流動特性，建立適當的數學和物理模型，用flunt進行數值計算。
  11. In this paper, two - dimensional and three - dimensional flow models in supersonic inlet and a simple reacting flow model in combustor and integrated flow field are established on the basis of k ? two - equation turbulence model and steady - compressible n - s equations, which are dispersed by finite volume method

    本文以定常可壓縮n - s方程作為控制方程，採用-雙方程模型作為湍流模型，分別建立了超聲速進氣道的二維、三維流場計算模型和補燃室及一體化流場的湍流燃燒模型，並採用有限體積法對控制方程進行離散。
  12. ( 1 ) the cfd model for the pulse combustion spray drying process. the computational fluid dynamics ( cfd ) based on the two - phase flow theory was employed in this paper, which used the standard k - e model and the particle trajectory model to simulate the gas - particle flow in the drying chamber. the momentum, heat and mass transfer regarding both gaseous and particulate phases during the spray drying inside the drying chamber was also revealed

    為解決這一難題，本文利用氣體一顆粒兩相流理論和計算流體力學（ cfd ）技術，建立了更符合實際噴霧乾燥過程的數學模型即噴霧乾燥的cfd模型，並進行了脈動燃燒噴霧乾燥過程模擬，其主要內容如下： （ 1 ）建立了脈動燃燒噴霧乾燥的cfd模型該數學模型建立在氣體一顆粒兩相流基礎之上，用標準k -模型預測乾燥室內的氣體湍流運動過程，顆粒軌道模型追蹤乾燥室內顆粒群的運動軌跡，熱質傳遞模型描述空氣和液滴的熱質傳遞過程。
  13. On basis of the modeling results, the effects of mach number, attack angle and ramp angle on the inlet performance are analyzed

    根據此數學模型，分析了攻角和進口氣流馬赫數對進氣道性能的影響，同時給出了斜板對進氣道性能的影響。
  14. In this thesis, hypersonic sidewall compression inlet ' s self - starting characteristics are numerical simulated and tested. with increasing mach number of inflow gradually, the hypersonic sidewall compression inlets can self - start. compared with the hypersonic sidewall compression inlet starting directly, characteristics are different. moving cowl, decreasing interior contraction ratio also can realize the hypersonic sidewall compression inlet ' s self - starting because of separation bubble on sidewall spilling out

    其次，在數值模擬結果的基礎上，設計了實驗模型和裝置並在馬赫3 . 85的風洞中進行了移動唇口板減小內收縮比實現側壓式進氣道自起動的風洞實驗，驗證了數值模擬的結果。
  15. So the flow field visualization in intake duct was realized. according to the experimental requirements, tow different transparent intake duct model were designed. a real - time holographic interferometry measuring system was developed, in which he - ne laser was used as light source, and a ccd ( charge coupled device ) video camera was used to grab the interferogram. a intake simulation system was build - up

    本文根據研究要求，用甲基丙烯酸甲酯製作了兩種不同類型的進氣道透明模型；設計並建立了利用he - ne激光器做光源的實時全息干涉測量光學系統；設計了一套能夠模擬進氣道在某一氣門升程時的進氣系統，用mtv - 1802cbccd攝像機對干涉條紋進行了實時採集。
  16. 4 ) the inspection method to the collision and interference during the placement course is studied and realized. the function module of dynamic simulation to the placement course is developed. at last, the placement information building on s - inlet of certain aircraft is checked by that inspection method and validated by real robot

    4 ）研究實現了鋪絲過程碰撞干涉檢測功能，開發了鋪絲過程動態模擬模塊，以某飛機s型進氣道為對象進行了驗證，證明了以上各工作的正確和有效性。
  17. In this paper the model of pill flying outer ballistic trajectory is established, and the aerodynamic force calculating method is given. the author set forth the relation of small caliber gun currency firing table and ballistic trajectory consistency, and give testing relation formula of small caliber gun cartridge ballistic trajectory consistency ; at the condition of navy 37 millimeter gun, the design of improved shrapnel currency firing table project is studied ; the data of shooting experimentation is analyzed, and have contrast analysis with theory calculating result. give better improved shrapnel project, and the ballistic trajectory consistency experimentation show that the project satisfy the request of the ballistic trajectory consistency

    本文應用了彈丸飛行時的外彈道模型並結合彈丸的氣動力計算方法，分析了小口徑艦炮通用射表與彈道一致性的關系，並給出了小口徑艦炮彈藥彈道一致性的檢驗關系式，研究了在海37艦炮的條件下對改進榴彈通用射表方案的設計，進行了對空射擊試驗數據的分析，並與理論計算結果進行了對比，給出了相適宜的改進彈方案，並經彈道一致性試驗驗證該方案滿足彈道一致性要求。
  18. By the use of discrete phase model, the gas - solid two phase flow under different conditions were simulated. the trajectories of particles were obtained, and the influence of secondary air and particle diameter distribution were investigated. and by the compare of experimental results and numerical simulation results, the reference for the further study of numerical simulation of gas - solid two phase flow in cfb was supplied to some degree

    運用顆粒軌道模型對床內不同工況下的離散相顆粒軌跡進行了數值模擬，得出了二次風、床料粒徑分佈等因素對顆粒軌跡的影響情況，並通過模擬結果與實驗現象的對比，為循環流化床內氣固兩相流動的進一步數值模擬研究提供了一定的基礎。
  19. Analysis the key geometry parameters of helical intake port modeling. a parametric three - dimensional model is achieved by interaction

    分析了柴油機螺旋進氣道建模的關鍵幾何參數，交互完成氣道參數化三維模型的建立。
  20. The results attained are as follows. on account of the strongly coupling character of parameters which have an effect on scramjet performance, the approximate evaluation models of scramjet inlet diffusion performance and the ignition problem in direct - connected experiments are established by neural network methodology

    針對發動機性能影響因素強烈耦合的特點，採用bpnn和rbnn神經網路方法，分別建立了超燃沖壓發動機進氣道擴壓性能和直連式發動機點火性能的神經網路近似評估模型，得到了很好的逼近效果和預測能力。
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