進氣道性能 的英文怎麼說

中文拼音 [jìnqìdàoxìngnéng]
進氣道性能 英文
inlet characteristic
  • 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） ...
  • 性 : Ⅰ名詞1 （性格） nature; character; disposition 2 （性能; 性質） property; quality 3 （性別） sex ...
  • 能 : 能名詞（姓氏） a surname
  • 氣道 : air flue; air passage
  1. The calculation results indicate that the starting performance of forebody / inlet with wedge - shaped lip is better than that with plane lip at low flight mach number. at high flight mach number, the performance of the forebody / inlets designed by the two methods is approximate. at low flight mach number, the starting performance of forebody / inlet designed by the method of constant shock wave intensity is better

    結果表明：唇口帶楔角的進氣道在低飛行馬赫數下的起動性能優于唇口平直的進氣道；採用等激波強度和等激波角度方法設計的進氣道在高飛行馬赫數下的性能相近，在低飛行馬赫數下，採用等激波強度方法設計的進氣道起動性能較優。
  2. At the same time, combining the electrostatic measurement principle and the actual working conditions of pneumatic pipelines, the author puts forward the design principle in theory and finishes the devising, executing, debugging, experimenting and analyzing the experiment phenomena and results, testing the feasibility of the electrostatic sensor to be used in the measurement on the mass flow rate of the coal paniculate. furthermore, with the debugging and experimenting of the system, the author improves the electrostatic sensor and its signal collecting system gradually according to the problems, and makes the performance of the system to be enhanced remarkably

    同時，作者結合靜電測量原理以及氣力輸送管道的實際工況，從理論上提出了靜電傳感器的設計依據，完成了靜電傳感器及其信號採集系統的設計、製作、安裝、調試和實驗，分析了實驗現象和結果，驗證了靜電傳感器用於煤粉質量流量測量的可行性，並且通過系統調試和實驗，針對發現的問題對靜電傳感器及其信號採集系統不斷地進行了改進，使其性能有了顯著地提高。
  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. According to the measuremental data of the two ammunications, the anti - designed computation and analysis of aerodynamic characteristic, flight stability, exterior ballistic characteristic for the two ammunications are studied with the advanced methods of the exterior ballistics. using the monte calo algorithm, the statistic mathematical model about ammunication ' s intensity is established and the 1000 miter vertical target intensity and the fall intensity are discussed in detail for the two ammunications. the improval potential and the main technical approachs of these ammunication ' s exterior ballistic performances are presented by compositive optimal algorithm

    根據工廠對俄ak130艦炮彈藥的測繪數據，利用先進的外彈道數值分析方法對兩種彈藥的空氣動力特性、飛行穩定性特性、外彈道特徵量等進行了反設計計算分析；採用montecarlo方法，建立了艦炮彈藥密集度性能統計分析數學模型，對兩種彈藥的立靶密集度和地面密集度進行了詳細的計算分析；利用外彈道性能綜合優化設計方法對兩種彈藥的外彈道性能指標的改進潛力和主要技術途徑進行了分析。
  5. The existence of angle of attack reduces the inlet performance

    攻角的存在也在一定程度上降低了進氣道性能。
  6. Sum up, the study of intake port is significant for the design of intake port and the development of engine. at present, the study of flow characters in intake port of engine mainly depends on experiment. numerical simulation is not universal, especially for the engine with dual - intake port

    目前，國內對發動機進氣道的流動特性研究手段主要依靠實驗，在實驗臺上進行大量的實驗，既費時又費力，實驗方法顯得過于陳舊過時，已不能適應現代高性能發動機研製工作的需要，因此，採用多維數值模擬技術是一種有效的研究手段。
  7. A ceramic coating is applied to the inner surface of the inlet duct to protect the composite from the high temperature

    由於復合材料耐高溫性能差，該進氣道在內部使用防熱陶瓷塗層進行熱防護。
  8. 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。
  9. 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。
  10. One of these models is chosen as a better scheme based on the one - dimensional calculation results

    通過一維的計算方法，經比較九種方案的性能參數，選取了性能較優的一種進氣道方案。
  11. 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。
  12. Comparisons by means of numerical simulation are made between this inlet and the normal two - dimensional ramp inlet

    數值模擬結果表明，設計工況下該進氣道能夠獲得跟常規二維斜楔式進氣道大致相當的氣動性能。
  13. The improvement of the flow character in intake port improves the dynamic characters and economy. all this can be used to reduce the cost

    提高進氣道的流動性能，可以提高發動機的動力性和經濟性，這是降低經濟成本的有效方法之一。
  14. The software fluent was employed and the two - dimensional flow field and performance parameters of four hypersonic / inlet models at design and off - design condition are obtained

    採用fluent軟體對所設計的進氣道設計點和非設計點二維流場和性能進行了數值模擬。
  15. The lpg - fueled engine is modified and optimized using electronic controlled fuel injection technology ; the comparison of engine performance with direct injection, intake liquid injection and gas injection has been done. the air fuel ratio, ignition timing and injection timing of the engine has been optimized and calibrated

    本文利用電控噴射技術對lpg發動機進行改造和優化，對比研究缸內直接噴射、進氣道液態噴射和氣態噴射的發動機性能，並對空燃比、點火提前角和噴射時刻等控制參數進行優化和標定。
  16. An experimental study on intake - ports characteristics of a four - valve diesel engine

    四氣門柴油機進氣道性能的試驗研究
  17. Other content in this paper is the design and investigation of spiral inlet port. the geometries that compose intake port have been repeatedly when intake port scheme was designed. the intake port scheme has been carried out steady - flow test. the experiment data has been analyzed and investigated, then the performance of inlet port has been estimated by the fluid coefficient and the whirl ratio. at last, the spiral inlet port scheme has been selected based on matching relation of the factors of combustion system. in addition, how to " intake port synthesis performance coefficienf ' evaluate engine intake port has been discussed

    本文的另一項內容是螺旋進氣道的設計和研究。通過對進氣道的幾個主要結構參數進行反復修改擬定進氣道方案，並對其進行穩流試驗，分析和研究試驗數據，利用流通系數、渦流比進行進氣道性能評估，根據燃燒系統要素的匹配關系，確定了兩種螺旋進氣道方案。另外，本文探討了「進氣道綜合性能系數」對發動機渦流進氣道性能的評估能力。
  18. 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。
  19. 2 - d, axisymmetric, and sidewall compression scramjet inlets flow fields are calculated and the performance of each inlet is analyzed. configurations of generic sidewall compression scramjet inlets are introduced and two kinds of spillage are introduced respectively

    然後對二維壓縮、軸對稱壓縮和側壓式進氣道的性能進行了計算，分析了進氣道在設計狀態和非設計狀態的性能。
  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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