supersonic combustion 中文意思是什麼
supersonic combustion
解釋
超音速燃燒- supersonic : adj. 【物理學】超聲波的；【航空】超音速的。 n. 1. 超聲波[頻]。2. 〈口語〉超音速飛機。n. -s 超聲學；超音速學。
- combustion : n. 1. 燃燒，發火，點火。2. （有機體內營養料的）氧化。3. 騷動。
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In the range of flight mach number mo = 3 ~ 7, in order to take the advantage of ramjet and scramjet, a fix - shaped dual - mode scramjet, in which both subsonic and supersonic combustion can be obtained, is used for hypersonic vehicle
在飛行馬赫數m _ = 3 - 7的范圍內，為充分發揮沖壓發動機的性能優勢，高超聲速飛行器採用了既能在亞聲速燃燒模態，又能在超聲速燃燒模態下工作的固定幾何形狀的雙模態沖壓發動機。 -
Both advantages of rocket engine and air - breathing engine are integrated into one kind of propulsion system, called rocket - based - combined - cycle ( rbcc ), which has multiple operating woke modes, including ejecting, subsonic combustion, supersonic combustion and rocket mode, with each mode operating at varying flying stage. rbcc has prominent potential of high efficiency and low cost, and so it is recognized as an advanced propulsion system of future single - stage - to - orbit reusable spacecraft and hipper - sonic missile. it has been broadly investigated in foreign countries and has been progressed into small and full - scale flying stage
火箭基組合動力循環（ rbcc ， rocketbasedcombinedcycle ）將傳統的火箭發動機和吸氣式發動機的優點集中組合到一個具有多種工作模態（包括引射、亞燃、超燃及火箭模態）的發動機里，在不同的飛行階段啟用不同的工作模態，因此具有大幅提高航天推進系統經濟性與高效性的潛在優勢，並可能發展成為下一代單級可重復使用航天器以及高超聲速導彈武器的動力系統。 -
To analyze particularly the shear flow and chemical reaction procedure occurred in supersonic turbulent combustion field, supersonic combustion mechanism is surveyed on by reading papers thoroughly
為細致分析超音速湍流燃燒流場的剪切流動及化學反應過程，針對超音速燃燒機理進行了深入的文獻調研。 -
Application of plif in research on supersonic combustion
平面激光誘導熒光技術在超聲速燃燒中的應用 -
Scramjet combustor may realize the subsonic - combustion mode and supersonic - combustion mode respectively based on the control of fuel in variable flight conditions. isolator has great effect on mode transition and preventing unstart of inlet. inlet can be unstarted by raising the back pressure result from chemical energy release in the combustor
計算研究表明，在相同的來流條件下，供油規律對燃燒室的工作模態有著重大的影響；在不同的來流條件下，可以通過調節供油規律使燃燒室分別實現亞燃模態和超燃模態；隔離段對防止燃燒引起的壓力升高對進氣道的干擾和燃燒室的模態轉換具有重要的作用。 -
Combustion with releasing heat effectively in supersonic flow is one of the most important, as well as the most difficult, technologies in researching and developing supersonic combustion ramjet
超音速流動狀態下的高效燃燒過程是研製超燃沖壓發動機最重要也是難度最大的關鍵技術之一。 -
Based on it, the performances of all kinds of supersonic ejectors are compared and the effects of variety of input parameters on the performances of supersonic ejectors are discussed. the conclusion is reached, that the design scheme of small ejecting coefficient, high ejecting mach - number, combustion - gas driving should be adopted to develop high performance, high compression - ratio prs. thirdly, the method of computational fluid dynamics is used to numerically solve the flow - field of the annular supersonic ejector with or without a second flow
接著，推導了超聲速引射器各種一維理論模型，並應用一維理論公式分析、比較了各種超聲速引射器的性能及其變化規律，全面探討了各設計參數對超聲速引射器性能的影響，得到了高性能、大壓縮比引射器系統應該採用小引射系數、高引射馬赫數、燃氣引射、優化超聲速引射器設計方案的結論。 -
The flame holding technology based on cavity in supersonic combustion was studied systematically and comprehensively. the interaction between gas / liquid injection and cavity flow were studied in non - reaction flows
論文選取基於凹腔的超聲速燃燒火焰穩定技術為研究對象，對凹腔燃燒流動過程和凹腔火焰穩定器性能進行了全面深入研究。 -
By simulated supersonic combustion in ‘ double - chamber ’, wall - pressure value is compared with experimented data. the simulated values accord well with experimented data
通過對「雙燃室」結構的數值模擬，將壁面壓力值與實驗值對比，其計算值較好地符合了實驗值。 -
Preliminary experimental investigation on supersonic combustion phenomena with shocktunnel
激波風洞中超聲速燃燒現象的初步實驗研究
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