thrust chamber 中文意思是什麼

thrust chamber 解釋
火箭發動機推力室
  • thrust : vt （thrust）1 猛推，沖；猛撳，沖入，插入，推入（出），突出，伸出，塞，刺，戳，戳穿。2 逼迫，把[...
  • chamber : n 1 〈古、詩〉室，房間；寢室，臥室；〈pl 〉套房；〈pl 〉律師[法官]辦公室。2 會議室，會場；議會，...
  1. 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。
  2. The investigation shows that plenum chamber total pressure has multifarious effects on arcjet thruster operation, and both specific impulse and thrust efficiency can be improved by increasing it befittingly under steady arc

    研究表明，集氣腔總壓對推力器工作過程具有多方面的影響，在保證電弧穩定的情況下，適當提高集氣腔總壓可同時提高比沖和推進效率。
  3. 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。
  4. 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。
  5. Calculating result showed : the thrust changing caused by the magnitude of at / ac was more larger than that both of the pressure index : " n " and of the chamber diameter, and the best thrust could be get when at / ac < 0. 3

    由數值計算可知， at ac的大小變化所引起的推力變化比壓力指數n和藥室直徑的變化引起的變化大得多，而且當at ac 0 . 3時，可以得到最佳的推力效果。
  6. Geometric, kinetic, and lifetime analysis of anti - rotation mechanism with thrust ball - bearing is conducted, which is commonly employed in the scroll compressor of automotive air - conditioning system, and its wear during later stage ' s operation is also analysed quantitatively. it is pointed out that, in the case of having radial flexible mechanism, the wear between anti - rotation mechanism and scroll wrap exhibits synchronism and self - compensation. otherwise slight rotation would take place with that mechanism and orbiting scroll, resulting in asymmetric pressure within compression chamber pair and radial leakage

    針對汽車空調渦旋壓縮機中最常見的防自轉機構滾珠防自轉止推軸承，進行了幾何、受力及壽命分析，並對其後期磨損加以定性的理論分析.指出在具有徑向柔性機構的情況下，該防自轉機構和渦旋盤齒的磨損具有同步性和自動補償性.在無徑向柔性機構的情況下，防自轉機構和渦旋盤會產生微自轉，可導致壓縮腔對壓力不對稱和產生徑向泄漏
  7. 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。
  8. 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。
  9. When the propellant was lead styphnate and nickel hydrazine nitrate, their properties of ignition and thrust were investigated under different chamber diameter and different proportion of the mixed propellant. the influence of different thruster parameters on thruster properties was calculated

    研究了史蒂酚酸鉛和硝酸肼鎳在不同藥室直徑和藥劑配比下的點火和推進性能，並且計算了推力器參數對推力性能的影響。
  10. Heat transfer characteristics of platelet transpiration - cooling thrust chamber

    多斜孔層板發散冷卻流動傳熱特性
  11. 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。
  12. Design method of multiperforated grain for single - chamber dual - thrust rocket motor

    火箭發動機單室雙推力多孔裝藥設計方法
  13. 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。
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