方噴管 的英文怎麼說

中文拼音 [fāngpēnguǎn]
方噴管 英文
blow line
  • 方 : Ⅰ名詞1 （方形; 方體） square 2 [數學] （乘方） involution; power 3 （方向） direction 4 （方面） ...
  • 噴 : 噴動詞1. （液體等受壓力而射出） spurt; spout; gush; jet 2. （噴灑） spray; sprinkle
  • 管 : Ⅰ名詞1 （管子） pipe; tube 2 （吹奏的樂器） wind musical instrument 3 （形狀似管的電器件） valve;...
  1. The aerodynamic design of curve of nozzle adopts perfect gas cresco method to calculate non - existence glutinous model surface, the correct boundary layer of the nozzle wall side adopts sivells - payre method, and the calculation of constringency part of the nozzle adopts stock formula

    其中，噴管型面氣動設計採用理想氣體的cresci方法計算無粘型面;噴管的附面層修正採用sivells - payre方法;噴管收縮段的設計採用維托辛斯基公式。
  2. 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。
  3. The main achievements are summarized as follows : ( i ) the m8 nozzle contour is designed by the characteristic line and the bound layer correction. based on the m7 nozzle, the m8 nozzle is designed by throat approximation

    全文取得了如下成果: （一）用特徵線加附面層修正的方法設計了m8型面噴管，並在m8噴管的基礎上採用喉道擬合的方法生成m7噴管。
  4. The effects of reynolds number, back surface of nozzle, aft - dome configuration and degree of submergence on aft - end internal flow were studied by both cold gas simulation and numerical simulation. it is showed that the separated flow is sensitive to the change of reynolds number and aft - end cavity configuration

    最後，利用冷流模擬與數值模擬相結合的方法，研究了雷諾數、噴管背壁形狀、后封頭形狀和潛入深度對燃燒室尾部流場的影響，結果表明流動的分離對雷諾數和背壁區幾何邊界的變化很敏感。
  5. Based on the comprehensive analyses of the various solutions in rarefied gas dynamics and the fact in this research, the modeling and calculation for the flow in micro nozzle are carried out by using the direct simulation monte - carlo method, and the analysis of internal flow variations under some different working conditions are performed

    在綜合考慮了稀薄氣體動力學問題各種解法和本課題實際研究的基礎上，本文採用直接模擬蒙特卡羅方法（ dsmc ）對微噴管內流場進行建模和計算，並分析了各種工況下的內流場變化。
  6. This paper studies the diffuser ' s influence on the fadw ' s running properties experimentally including the inner wall and outer wall of diffuser and the backpressure of the diffuser. to prevent the gas of fadw from leaking into the laser cavity because of the effect of layer and turbulence the leak - proof flakes are designed. first the method of the leak - proof flake design is studied and then its influence on the properties of fadw is studied experimentally

    實驗研究了擴壓器對fadw工作性能的影響，提出了擴壓器結構和超音速噴管相對布局參考數據；研究了氣動窗口側壁防漏片的結構對氣動窗口性能的影響，並給出其工程設計方法；同時還研究了擴壓器不同的背壓對整個fadw作性能的影響，據此提出了擴壓器與引射器結合的設計方案，從而為大壓比、高性能的fadw的設計提供了進一步設計參考方法。
  7. The application background of thrust vectoring technology on aircraft and its advantages are analyzed. the main characteristics of some type of vectoring nozzles are discussed, the expression of thrust vectoring force and moment are set up. then, the nonlinear motion equations of aircraft with three axes of thrust vectoring are deduced

    本文主要針對推力矢量飛機非線性飛行控制的理論和應用問題進行了一定的探索和研究，進行的主要工作有： 1 、研究了推力矢量在飛機上的應用背景和收益，分析了現有推力矢量噴管的主要形式和特點，給出了推力矢量力、力矩的數學模型，並在此基礎上推導了帶三軸推力矢量飛機的非線性運動方程，為控制律的設計奠定基礎。
  8. The sprayersare equipped with spraying nozzles of two different types and different functions, through which airflows of different shapes burst forth for different purposes. when used together with lengthened spraying hose, brushes and glass blades, the sprayers can show more excellent convenience and better effects

    配有2種不同形狀及功能的噴嘴，可分別噴出不同形狀的氣流，可供不同的使用選擇加長噴管、刷頭、玻璃刮刀的配合使用，可使清洗更方便，效果更好。
  9. The results show that to design a supersonic / hypersonic nozzle of wind tunnel must consider the effect of variable specific heat, which gives reference to nozzle and wind tunnel design

    考慮這一因素后，噴管出口馬赫數接近設計馬赫數，其設計精度有較大提高。本方法可為超音速高超聲速噴管設計和反設計提供參考。
  10. To prove the accuracy of the mach number, and the parameter homogeneity of the design nozzle " s exit, cfd calculate has carried on the design results. under the condition of supersonic and hypersonic flow, and a certain range of temperature, and mach number, the conclusion of the influence of specific heat to nozzle design is drawn

    為了驗證所設計的噴管出口馬赫數的大小和噴管出口流場的均勻性，採用nnd格式和b l湍流模型求解雷諾平均n - s方程，對設計結果進行了cfd驗算，得出了在一定溫度范圍內，超音速、高超聲速流動的條件下，不同馬赫數范圍內變比熱容對噴管型面和噴管出口馬赫數的影響。
  11. To meet the needs for wider surge margin of the turbofan engine, a new model was developed to predict the characteristics of the fan / high pressure compressor and turbine in this thesis. several ways, including, variable inlet guide vanes of the fan, variable guide vanes of the high pressure compressor, the variable inlet area ratio of the mixer and the nozzle areas, were presented to enlarge the surge margin of the turbofan engine. meanwhile, a method of combined variable geometries for optimizing controls of inlet guide vanes of the fan, guide vanes and the first two stators of high pressure compressor, area ratio of mixer and noz zle areas was established

    為了滿足下一代作戰飛機對推進系統的性能和穩定性要求，本文建立了壓縮系統特性和渦輪特性的新模型，並分別採用改變渦扇發動機風扇進口導流葉片、壓氣機導流葉片和前兩級靜葉片、混合室進口處內、外涵面積比和尾噴管面積，研究了其對發動機性能和穩定性的影響，進而得出了渦扇發動機變幾何擴穩的方法，為發動機變幾何擴穩研究打下理論基礎。
  12. By increasing the length of laval nozzle, an approach was presented to obtain higher particle velocity necessary for gas - solid separation in dusty gas of high temperature and high pressure

    提出了用增加縮放噴管長度的方法，使含塵高溫高壓氣體中的灰塵顆粒獲得實現氣固兩相分離所必需的更高動量的途逕。
  13. Based on one dimension flow theory and lagrange method, the correlation of speeding rate of particles under gas flow drag with the size of particles and the length of laval nozzle used for the gas and solid two - phase separation test apparatus was studied

    摘要採用一元流動理論和拉格朗日方法，研究了用於氣、固兩相分離試驗裝置的縮放噴管內，被氣流拖曳的顆粒加速率與顆粒大小和縮放噴管長度的關系。
  14. In the aero - optical flow field tomography measurements, all projection data of different direction must be simultaneous. and the laser nozzle flow field up - stream and down - stream strehl ratio simultaneous measurements have the synchronicity requirement. the working environment of high power laser is rigorous and complicated

    在考慮了由於氣動光學流場層析測量中的多個投影方向數據的同時測量、激光器噴管流場上游和下游同時測量的同步要求，以及高能激光平臺的復雜環境多方面因素的基礎上，考慮了硬體匹配的一些問題，設計了一套高速的線陣s - h傳感器。
  15. As an example of 3d program with high quality mesh, proper boundary & initial conditions and ingenious simulation strategy, numerical analysis of flow - fields in hylte nozzle and cavity of dfcl running on fuel system of ( nf3 + h2 + he ) / d2 and experimental stagnation parameters, has been performed using vibration - state - unbalance & rotation - state - balance model, and a detailed kinetic model including 111 one - way primary reactions expressing by finite rate equations between thirteen species. the coefficients of transportation used in the analysis are calculated by employing the formulas of molecular kinetics

    新建立的三維程序在高質量網格、合理的初邊值以及模擬方案基礎上，採用振動非平衡?轉動平衡模型和有限速率方程表達的111個單向基元反應的化學動力學模型，利用分子運動理論計算的輸運系數和工程實驗採用的滯止參數，對運轉（ nf _ 3 + h _ 2 + he ） d _ 2燃料體系的df激光器的hylte噴管和光腔進行了數值模擬分析。
  16. In the experiment, the infrared radiation and axial distribution of wall temperature and near wall flow pressure were measured with and without film cooling

    得到了各冷卻方案噴管的壁面壓力分佈、壁溫分佈和紅外輻射特性。
  17. The flow field of fadw is very complicated, especially in the free vortex jet zone. so the method is according to the ideal flow, including the design of the asymmetric supersonic laval nozzle and the diffuser

    所以，本文所建立的fadw的基本設計方法是理想狀態下的設計方法，其中主要包括非對稱超音速噴管的設計和氣動窗口擴壓器的設計方法。
  18. In this paper, a three - dimensional ( 3d ) program for the three - dimensional reactive flow fields of complicated geometric nozzle, which governed by the compressible full navier - stokes equations with realizable k - s turbulent model, has been upbuilt by using full implicit couple arithmetic and fvm ( finite volume method ) based on understanding and assimilation of a two - dimensional program group of cr ( chamber - radon ). the new program fulfils the urgent need of numerical tools for simulating three - dimensional reactive flow - fields of hylte ( hypersonic low temperature ) and other latest nozzles, for which cr is out of action in simulation, and can be applied to simulate other chemical laser system, such as chemical oxygen iodine laser ( coil ), overtone fluoride hydrogen, all - gas iodine laser, and so on. furthermore, some related topics about nozzles design and engineer ing also have been discussed

    本文在二維cr （ chamber ? radon ）程序研究的基礎上，採用有限體積方法和完全隱式的耦合演算法，通過求解帶realizablek -兩方程湍流模型的多組分、有反應的三維完全納維埃?斯托克斯（ n ? s ）控制方程，建立了一套能夠對復雜形狀的三維噴管和光腔進行數值模擬的三維程序，解決了連續波df hf化學激光器增益發生器設計缺乏三維數值模擬工具的問題，並用該工具解決了cr程序無法實現的hylte等復雜三維噴管流場的理論模擬問題。
  19. The minimum requirement for supersonic separator to accomplish its basic function is that the flow inside the separator must be at the critical state at the laval nozzle throat and its flow rate must be equal to its critical flow rate, or the dehydration performance will deteriorate

    改進旋流器的設計，使其摩阻盡量小，從而使激波向遠離laval噴管喉部方向移動，可以有效改善分離管的工作性能。在目前所設計的三個旋流器中，旋流器a的
  20. Using axisymmetric full navier - stokes equations, the thermo - chemical nonequilibrium flow in hypersonic nozzle was simulated and the scale effects due to nonequilibrium were analysed numerically

    摘要採用軸對稱熱化學非平衡全n - s方程，數值分析了高超聲速噴管流場中非平衡引起的尺度效應。
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