氣壓發動機 的英文怎麼說

中文拼音 [qìyāfādòngjī]
氣壓發動機 英文
air pressure engine
  • 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...
  • 壓 : 壓構詞成分。
  • 發 : 名詞（頭發） hair
  • 機 : machineengine
  • 氣壓 : [氣象學] pressure; atmospheric pressure; barometric pressure; gas pressure; air pressure
  1. Tahir r b, molder s and timofeev e v. unsteady starting of high number air inlets - a cfd study [ r ]. aiaa 2003 - 5191

    梁德旺，袁化成，張曉嘉.影響高超聲速進氣道起動能力的因素[ c ] / / 2005年沖壓發動機技術交流會論文集， 2005
  2. Jacv jet air control valve

    增壓發動機壓燃室空氣噴射控制閥
  3. For studying the performance of solid rocket ramjet under the influence of different flight conditions, it ' s significant to simulate the integrated flow field of inlet and combustor

    因此，開展超聲速進氣道/補燃室流場一體化數值模擬研究對于考查飛行狀態對於火箭沖壓發動機性能的直接影響具有重要的現實意義。
  4. Based on detailed analyze on turbine engine and ramjet, a new conceptive internal - rotor burnt rotating ramjet ( irbrr ) with an rotating cylinder in the center of rotor in which the revolved stream can be ram - compressed and burnt has been proposed and some primary research have been done as below : the scheme of structure, principles, thermodynamic cycle and performances of the new conceptive engine has been studied in the paper

    本文通過對燃氣渦輪發動機和航空沖壓發動機的原理結構進行詳細分析並進行融合創新，提出了一種利用內置旋轉汽缸進行旋轉氣流沖壓壓縮和旋流燃燒的新概念內置燃燒室旋轉沖壓發動機，並進行了一些前期的基礎性探索研究，具體研究內容有:對旋轉沖壓發動機進行了總體方案設計、工作原理分析、氣動熱力循環和性能分析等概念性研究。
  5. 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。
  6. The structure design and the performance research of supersonic inlet / combustor are key techniques for solid rocket ramjet

    超聲速進氣道及補燃室的設計與性能研究是固體火箭沖壓發動機的兩大關鍵技術。
  7. The performance of supersonic inlet determines the pressure and the air flux in combustor, then affect the work of ramjet

    超聲速進氣道的性能優劣決定了補燃室流場內的壓強和空氣流量，進而影響到沖壓發動機的工作性能。
  8. Dual - mode ramjet engine which gathers the advantages of both ramjet and scramjet is a new - style airbreathing propulsion device. it can operate over a wide mach number ranges ( m = 3 - 8 ). it is of remarkable performance and great potential application for hypersonic vehicle

    雙模態沖壓發動機是綜合了亞燃沖壓發動機和超燃沖壓發動機優勢的一種新型的吸氣式動力裝置，它可以在比較寬廣的飛行馬赫數范圍內工作（ m 3 8 ） ，具有良好的工作性能和廣闊的應用前景。
  9. There are great differences between ground test of a flight vehicle ' s aerodynamics and that of a dual - mode scramjet when ground test facilities are used to do experiments on a dual - mode scramjet engine, the components of incoming flow and its parameters, including total pressure, total temperature ( or total enthalpy ) and velocity must be simulated. at the same time, since the fuel ' s resident time within a combustor is very short, on the order of one millisecond, it is difficult to measure the flow - fields

    進行雙模態沖壓發動機地面試驗研究時，必須要求試驗設備能模擬實際飛行條件下來流氣體的組分、總壓、總溫（或總焓）以及來流氣體的流動速度；同時由於燃料在燃燒室內駐留的時間很短，一般為毫秒量級，從而使流場物理量的測定顯得非常困難。
  10. According to the definition and expression of the thrust, as well as the condition derived from them, a method of solid rocket ramjet thrust determination and its program are provided on the basis of engine ground simulation test

    本文以西北工業大學固體火箭沖壓發動機直連式試車臺為研究對象，探討固體火箭沖壓發動機地面試驗技術。首先，從推力的定義出發，建立了試驗中來流空氣流量、燃料流量與固體火箭沖壓發動機推力之關系。
  11. Research on combustion and emissions characteristics of diesel cng dual - fuel turbocharged ciengine

    天然氣雙燃料增壓發動機燃燒與排放特性研究
  12. 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； 3
  13. The flow fields of two - dimension for fuel - air equivalence ratio = 0. 35 are respectively calculated. comparisons made with experimental data obtained at similar ( but not identical ) flow conditions were encouraging

    得到了油氣當量比= 0 . 35的氫燃料超燃沖壓發動機燃燒室流場的精細結構。
  14. Gas flow control techniquc of rocket ramjct is discussed, and then some base idea and research achievements in the design of that are also expressed in the paper

    對固體火箭沖壓發動機燃氣流量調節技術進行了論述，闡述了固體火箭沖壓發動機燃氣流量調節技術在設計上的一些基本思想及研究成果。
  15. Under the base of the parameter characteristics of the engine thermodynamics and the air - inlet simulation, the measurement and control schemes are designed with virtual instrument technology

    本文在深入分析討論固體火箭沖壓發動機試驗參數特點以及進氣模擬對控制系統要求的基礎上，提出了發動機溫度、壓力、流量及其推力測量的總體方案和進氣模擬總體控制方案。
  16. Specially, the rotating ramjet with shaft power output was discussed. result showed that the thermodynamic cycle of the rotating ramjet is a breton cycle including two anti - cycle processes. because the advantage on thermodynamic performances and structure, the rotating ramjet will has wide prospective application in aircraft and powers system in heavy trucks, military facilities, tanks, warship as well as power plant

    著重討論了軸功輸出方案的旋轉沖壓發動機，初步分析表明，旋轉沖壓發動機的熱力循環是加進了兩個反循環的布雷頓循環，該發動機在熱力性能和結構方面與燃氣輪機相比有獨特優點，有望在現代和未來各類飛行器及各類重型車輛、戰略設施、坦克、艦船動力、電力等能源動力領域獲得廣泛應用。
  17. Also longitudinal aerodynamic characteristics of missile are investigated. the traditional dependence on wind tunnel experiment is changed greatly : firstly, the aerodynamic characteristics of missiles with complex configuration are solved satisfactorily, especially integral rocket - ramjet missile ; secondly, feasibility of n - s equation to numerical simulation of inner and outer fiowfield of missile with complex configuration is discussed

    （ 3 ）採用n - s方程方法數值模擬某型整體式沖壓發動機導彈的全彈內外流場，研究了導彈的縱向氣動特性，改變了過去依賴于地面風洞試驗結果的傳統做法。
  18. 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。
  19. The ram - compressed technology in ram - compressed rotor is the key of the rotating ramjet. we discussed it detailedly in some aspect such as theoretic analysis and numerical simulation and model test, and then point out that the essential of the ram - compressed technology is the air is compressed by the moving shock wave. the formula of parameter both sides the moving shock wave and

    指出了旋轉激波壓縮是旋轉沖壓壓縮的主要方式，推出了旋轉激波壓縮的參數關系式和沖壓轉子進氣道和盤腔中的簡化運動方程和壓力方程，並通過對冷態流場的數值模擬及模型試驗研究驗證了上述理論分析結果，為旋轉沖壓發動機沖壓轉子的設計分析奠定了理論基礎。
  20. The primary work of this paper is as follow : three aspects are analyzed in detail as to the characteristics of integral rocket - ramjet, which include : a. the matching for inlet shape and missile configuration ; b. the influence on missile conceptual performance caused by the number and position of inlet ; c

    具體表現在如下幾個方面： （ 1 ）針對整體式沖壓發動機的特點，詳細分析了進氣道型式與導彈總體布局的匹配關系、進氣道數目及其安裝位置對導彈總體性能的影響、沖壓發動機和固體助推器的一體化等彈機一體化設計的問題。
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