推力室 的英文怎麼說

中文拼音 [tuīlìshì]
推力室 英文
thrust barrel
  • 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...
  • 力 : Ⅰ名1 （力量; 能力） power; strength; ability; capacity 2 [物理學] （改變物體運動狀態的作用） forc...
  • 推力 : visatergo; soot; propulsive force; thrust; momentum thrust
  1. The anchor flange for west - fast gas pipeline project is a kind of important device to avoid axile thrust damages all valve of electric field and the anchor flange of the project are only supplied by my company. the anchor flange has replaced import product, filling up domestic blank and achieving nationalization.

    錨固法蘭是西氣東輸管道工程為防止軸向推力對各種站場閥室造成破壞而設置的一種重要裝置。全線所用的錨固法蘭均由我公司獨家供應。該產品代替了進口，填補了國內空白，實現了國產化。
  2. Some propellant droplets may not evaporate within the confines of the thrust chamber.

    有些推進劑可能在推力室內並未汽化。
  3. Progress of the composite thruster abroad

    國外復合材料推力室技術研究進展
  4. Different equations to corresponding components are presented by analysing and transformating the general equations of fluid routes, then static characteristics mathematical model of liquid propellant space propulsion system is presented. based on the data of static characteristics calculation, mass model of thruster, propellant, propellant tank, gas, gas bottle, pipe and valve is presented using both the method of statistical regression and the method of stress analysis, then corresponding mass model is presented. based on the characteristics of liquid propellant space propulsion systems, analyse the five phases ( concept and definition, design and improvement, manufactureing and arrangement, operation and ma intenance, disposal ) in which life cycle cost of liquid propellant space propulsion systems is cost separately, then discompsed structure of life cycle cost and model of life cycle cost are presented

    將組件分成氣路組件和液路組件，再對氣路組件和液路組件進行相應的分類，然後通過對通用流路方程進行分析和變換對不同類型的組件分別建立不同的方程，從而建立了一個適用於液體推進劑空間推進系統的靜態數學模型；根據靜態計算所得到的數據，應用統計回歸法和應力分析法分別建立推力室、推進劑、推進劑貯箱、氣體、氣瓶以及導管和活門等的質量模型，從而建立相應的質量模型；結合液體推進劑空間推進系統特點，對液體推進劑空間推進系統全壽命周期費用發生的五個階段（概念和定義、設計和改進、製造和安裝、運行和維修、處理）分別進行分析，建立了液體推進劑空間推進系統全壽命周期費用分解結構和全壽命周期費用模型。
  5. With the further economic growth and the implement of development of the western regions, hydroelectric construction in our country is undergoing rapid growth, anumber of high - dam power - station is in building or in programming. in view of its higher - head and larger magnitude of spill structure outlet, it is difficult for conventional concrete or reinforced concrete structure of pier and pier room to support its vast water pressure. coupled with the improvement of prestressed method, it has been the noteworthy tool in solving the problem

    隨著我國經濟的加速發展及西部大開發戰略的實施，我國水電事業也迎來了迅猛發展的大好時機，一批高壩水電站正在建設或規劃之中，其泄水建築物孔口及水頭愈來愈大，常規混凝土或鋼筋混凝土閘室閘墩結構難以承受如此之大的水推力作用，隨著預應力技術的成熟，這一技術已成為解決該問題的關鍵技術措施之一。
  6. Focusing on the performance evaluating and the design of tripropellant injector, adopting the cold test rig with background pressure supply, malvem particle analyzer, ccd photography system, tripropellant hot test - bed, numerical simulation software and auxiliary theoretical a nalysis, the d ischarge c haracteristic a s w ell a s a tomization p erformance o f the injector and the combustion performance as well as the mode - transition characteristic of thrust chamber are studied detailedly based on the 3 different structures of coaxial tripropellant injector, large numbers of important conclusions are gained

    本文圍繞三組元噴嘴的性能評定及設計方法。採用反壓冷試臺、馬爾文測粒儀、 ccd高速攝影系統、三組元發動機熱態試驗臺、數值模擬程序及輔助理論分析等多種技術手段和研究方法，對三種結構的同軸式三組元噴嘴深入進行了噴嘴流量特性和霧化特性、推力室燃燒性能和轉工況性能研究，得到了大量重要結果。
  7. A three layers thruster was designed. the middle layer was chamber, the top layer was ignition circuit and the bottom layer contained a diaphragm with several nozzles. it could integrate 4 micro - thruster which diameter was 0. 8mm on the diaphragm with 10 * 10 * 2mm

    在實驗中，設計了三層的推力器結構，中間為藥室，上層和下層為點火電路和帶噴管的蓋片，可以在10 10mm和2mm厚的板上集成了4個直徑為0 . 8mm的微推力器。
  8. 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。
  9. As to the experimental study, a test system was designed firstly, which include propellant feed system, cooling system, controlling system and measure system. secondly, a test engine was designed according to the experimental requirement. on this basis, experiments under different working conditions were done, and the results of them were analyzed, which showed the combustion efficiency and stability

    實驗方面，首先設計了針對三組元發動機推力室工作過程進行試驗的試驗系統，包括推進劑供應系統與冷卻水供應系統、控制系統以及壓力、溫度、流量的測量採集系統；其次，設計出符合試驗要求的縮尺發動機；最後針對所設計的試驗系統和發動機，進行了不同工況的試驗，對所得數據進行了分析處理，得到了不同工況下燃燒效率和燃燒穩定性特性。
  10. The results of static firing test shows that the thermal erosion properties, mechanical properties, tand thermal shock resistance of the c / sic composites can meet a demand for thermal - structure application in the area of aerospace such as liquid rocket thruster

    試驗發動機地面熱試車結果表明，該c / sic復合材料的力學性能、燒蝕性能和熱震性能優良，可滿足宇航工程中諸如液體火箭發動機推力室等對熱結構材料的使用性能要求。
  11. Heat transfer in four parallel connecting thrust chambers with radiation cooling was analyzed

    摘要分析了四機?聯全輻射冷卻推力室的熱特點。
  12. The result proves that the circular temperature change caused by the radiation between the chambers is mostly decided by the dimensionless distance l / d and is foreign to the original wall temperature

    計算表明，推力室之間的輻射傳熱引起的周向溫度畸變，主要取決于推力室間的相對間距l / d ，而與原壁溫水平無關。
  13. One approach consists of varying only the total flow thereby maintaining the same thrust chamber hardware.

    有一種方法是僅改變推進劑總流量，而推力室結構保持不變。
  14. The channel scale on transpiration cooling for the platelet thrust chamber of liquid propellant rocket engine is approaching micron dimension. it is very possible that micro - scale effects will occur in the flow and heat transfer of the channel. in the past, researchs on flow and heat transfer in the platelet micro - channel are mostly based on macro - scale theory

    液體火箭發動機推力室壁面發汗冷卻通道的尺度已達微米量級，通道內的流動與換熱很可能存在微尺度效應，以前的相關研究都以宏觀尺度的理論為依據，其研究結果的合理性需要進行微尺度效應的分析。
  15. On optimizing pin - fin shape for efficient cooling of turbine blades

    層板發汗冷卻推力室的傳熱特性
  16. The energy equation of the thrust chamber wall was developed by omitting radical heat conduction and only considering the radiation heat transfer of the four chambers, the radiation leakage through nozzle exit, the axial and circular heat conduction

    忽略徑向導熱，考慮推力室外向的相互及自身輻射交換、內壁經噴口的輻射泄漏以及周向和軸向的傳導熱量，建立了推力室壁的能量方程。
  17. In this paper, the characteristics of tripropellant rocket engine was studied in two different ways : experiment and simulation

    本文從實驗、模擬兩個方面對三組元液體火箭發動機推力室的工作過程進行了研究。
  18. The relationship between thermal contact resistance and surface roughness is discussed. the influence of outer space heat flow on spacecraft on the orbit is analyzed, and a balance temperature of spacecraft on the orbit is calculated

    通過計算空間外熱流對航天器在軌溫度的影響，得到航天器在軌平衡溫度。最後完成瞬態溫度場的模擬計算，對推力室在軌溫度進行數值模擬。
  19. As to the simulation, the inner flow field of thrust chamber was simulated. here the thrust chamber was treated as a two - dimension problem. the simulation model involved injection, mixing and combustion of gaseous propellant

    模擬方面，對三組元發動機推力室的穩態燃燒過程進行了數值模擬，分析了推進劑各組元和各燃燒產物組分在推力室內的分佈。
  20. Also, the analysis of the system with only one pair of operating thrust chambers was performed

    對僅有兩對角推力室工作、另一對推力室不工作時的溫度分佈特點也作了分析。
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