推進噴管 的英文怎麼說

中文拼音 [tuījìnpēnguǎn]
推進噴管 英文
propelling nozzle
  • 推 : 動詞1 （向外用力使物體移動） push; shove 2 （磨或碾） turn a mill or grindstone; grind 3 （剪或削...
  • 進 : 進構詞成分。
  • 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;...
  • 推進 : 1 （推動工作 使前進） push on; carry forward; advance; give impetus to 2 [軍事] move forward; dri...
  1. In recent years at iron - making plant of pangang, the coke ratio of pig iron has reduced evidently by insisting on “ burden preparation ” course, improving quality of sinter, raising wind temperature, increasing rich oxygen quantity and injecting abundant pulverized coal into bf. the solid fuel consumption of sinter has been decreased greatly through insisting on using high - quality calces, practising high feed sintering, actualizing many techniques in solving key problems. at the same time, the energy source base management has been strengthened, and energy - saving work has made great progress, profits generated by energy - saving have exceeded a hundred million yuan

    近年煉鐵廠通過堅持「精料」方針，改善燒結礦質量，提高風溫，增大富氧，實施大噴煤，使入爐焦比有明顯下降；燒結堅持用好生石灰，推行厚料層燒結，實施多項技術攻關，固體燃耗大幅度下降；同時加強能源基礎管理，節能工作取得長足進步，節能創效益1億元以上。
  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. Recommended practice for fire department operations in properties protected by sprinkler and standpipe systems

    用噴灑器和儲水管系統進行性能保護的防火部門操作推薦規程
  4. The transportable powder series extinguishers are effective extinguishing appliances, in which extingshing agent sodium bicarbonate or ammonium phosphate powder together with the driving gas - nitrogen are filled in a full - sealed container. during application, nitrogen drives to jetting powder for extinguishing, which is advanced in technology, simple in structure, convenient in operation, maintenance and storage, safe and reliable

    推車式乾粉系列滅火器是一種新型高效的滅火器材，它使用磷酸銨鹽或碳酸氫鈉乾粉滅火劑和驅動氣體氮氣一起灌裝在全封閉的容器內，滅火時由氮氣驅動乾粉滅火劑噴射滅火，具有技術先進，結構簡單、操作方便、易於維修、便於保管，安全可靠等優點。
  5. Abstract : this paper briefly presents th e application of advanced brazing techniques for a larye number of assemblies of space vehicles, such as thrust chamber and turbine rotor of launch rock et engine, titanium tube of satellite, attitude control engine injector and wave guide component of satell ite, reflector, tube and honeycomb panel of manned spacecraft, main engine nozzl e and preburner of space shuttle as well as the pipeline systems of space statio n

    文摘:簡略地介紹了先進釬焊技術在航天器部件，例如運載火箭發動機的推力室和渦輪轉子、人造衛星的鈦導管、姿控發動機噴注器和波導器件、載人飛船的反射器、導管和蜂窩壁板、航天飛機的主發動機噴管和預燃室以及空間站的管路系統等的廣泛應用情況。
  6. 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。
  7. In this paper, we focus on some typical nozzles of micron dimension being developed for micro - propulsion system in and abroad, and make modeling and simulation analysis of the performance of rarefied flow in the micro nozzle

    本文針對國外研製的微推進系統所用典型微米級噴管，對稀薄氣流在微噴管內的流動性能進行了建模和模擬分析。
  8. With the rapid development of micro - satellite technology in china, micro nozzle being the key component of the micro - propulsion system has been paid much effort of research, in this realm, the simulation of rarefied flow in the micro nozzle is the key step for the design and performance improving of micro nozzle

    隨著我國微小衛星研製的大力發展，作為微推進系統關鍵部件的微噴管研究成了重要的研究課題之一，對微噴管內流場稀薄氣流的模擬分析是微噴管設計和性能改善所需要解決的關鍵問題。
  9. Chapter ii : latent capacity and present conditions of water resource. first, the author introduced the total amount and distribution of water resource in the east and central area of gansu, and then discussed the current utilization and contradiction between supply and demand of water resource. and last, the author posed the measures and countermeasures of exploiting water resource. chapter iii : latent capacity and present conditions of land resource. first the author introduced the total amount and distribution of land resource. and then discussed the current conditions utilization and latent capacity of land resource

    對東中部地區的水資源總量、分佈和特點進行定量和定性的分析，以灌區水資源利用及供需矛盾為突破口，對水資源潛力開發的幾個關鍵問題進行了分析：加強與水資源相關的基礎問題的研究；強化水資源危機的意識，建立節水工農生產體系；建立流域水資源統一管理機構；強化節水農業科技成果的推廣轉化；逐步推行噴、微灌高新節水技術；充分利用化學調控技術提高作物抗旱性和水分利用效率；大力發展以集雨節灌技術為核心的集水農業。
  10. The comparision of the computation result and the experimental data shows that prediction of ka series propeller by surface panel method is feasible

    本文嘗試建立一種面元法預報導管螺旋槳水動力性能的方法，為設計導管螺旋槳和研究泵噴射推進裝置建立基礎。
  11. The conclusion that the optimal secondary nozzle exit area generating the maximum thrust agrees well with the numerical simulation, indicating that the exit area of secondary nozzle should be optimized according to structure and flow parameters during design

    表明在引射火箭設計時，應結合引射火箭的結構和流動參數對二次噴管出口面積進行優化設計，以達到最佳推力性能。
  12. 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。
  13. In addition, the usaf continues to fund development work of the aerojet ( formerly atlantic research ) variable flow ducted rocket ramjet system as a future propulsion option for an extended range aam

    此外，美國空軍繼續投資于航空噴氣研究所（原來的大西洋研究所）的可變噴流管火箭發動機系統，將其作為增程空空導彈的未來推進選項。
  14. When liquid propellants are used the fuel and oxidize are fed under pressure to one or more combustion chambers and expanded to atmosphere through convergent-divergent nozzles.

    當使用液體推進劑時，在壓力作用下，燃料和氧化劑輸送到一個或幾個燃燒室中，並通過收斂-打散噴管，排到大氣中。
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