推進劑流量 的英文怎麼說

中文拼音 [tuījìnjìliúliáng]
推進劑流量 英文
propellant flow
  • 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。
  • 劑 : Ⅰ名詞1 （藥劑; 制劑） a pharmaceutical or other chemical preparation 2 （某些有化學作用的物品） a...
  • 流 : Ⅰ動1 （液體移動; 流動） flow 2 （移動不定） drift; move; wander 3 （流傳; 傳播） spread 4 （向壞...
  • 量 : 量動1. （度量） measure 2. （估量） estimate; size up
  • 推進 : 1 （推動工作 使前進） push on; carry forward; advance; give impetus to 2 [軍事] move forward; dri...
  • 流量 : rate of flow; flow; runoff; discharge; throughput; （flow） rate; quantity （of flow）; flux
  1. 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。
  2. When nals was used as the collector in the process, the optimal conditions were the ph of feed solution 5. 0 - 6. 0, air flow rate 100ml / min, the liquid column depths 20cm, the surfactant concentration determined by its cmc and feed concentration. under this condition, the 3 can be above 20. also, the optimal ph ( 5. 0 ) was calculated theoretically for the recovery of the cu ( ii )

    對以十二烷基硫酸鈉為捕集劑的泡沫吸附分離過程的工藝參數進行了研究，並得出本分離系統所確定的最佳工藝參數為： ph5 . 0 6 . 0 ，氣體流量100ml min ，液位高度20cm ，最佳表面活性劑濃度由其臨界膠束濃度和原料液濃度確定，此時（濃縮比）可達20以上；同時還從理論上推算出泡沫吸附分離銅的最佳ph值范圍為5 . 0左右。
  3. Much works has been distributed to the development of a vacuum system to simulate the outer space and a measurement system to test the arcjet performance. ignition experiments in various operational modes have been done with argon as propellant. macroscopical working parameters including thrust, mass flow rate, voltage, current, inlet pressure and vacuity are obtained by the test measurement system and actual performance parameters including specific impulse, thrust efficiency, ratio of thrust and power and ratio of power and mass flow are calculated

    以氬氣作為推進劑，在不同工況下進行點火實驗，測量獲得了其工作推力、電弧電壓和電流、推進劑流率和弧室壓力等宏觀參數，得到了不同實驗條件下其工作的實際比沖、推力效率、推力/功率比以及比功率等性能參數，分析了推進劑質量流率、電弧功率、電弧加熱發動機電弧室結構尺寸等因素對其性能的影響，為數值模擬研究和實際的低功率電弧加熱發動機優化設計及研製提供了實驗基礎。
  4. Boron coated with different content ap on the rheological properties of the slurry containing 30 % boron have been carried out with the help of the sv2 / sv2fl measuring system in haake rotary viscometer. the experimental results reveal that the rheological properties of the slurry of boron coated with 20 % ap is best, namely, the slurry has a good levelability and a long pot life. the optimum conditions in the preparation of the boron - based propellant with 30 % boron in weight were obtained, and a technical and theoretical foundation has been established for the formulae determination

    3 、用進口haake旋轉粘度儀對不同包覆硼粉在硼含量為30以上的實驗配方藥漿中的流變特性研究，篩選出用20 ap包覆的硼粉所製成的藥漿不僅流平性好而且適用期長，同時找到了含硼量為30的高含硼量推進劑藥漿成功研製的成熟工藝過程及條件，為配方的進一步定型奠定了較扎實的技術和理論基礎。
  5. 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。
  6. 4. in order to further improve and raise storage, energy and combustion properties of boron - based fuel - rich solid propellant, while the present slurries of boron - based fuel - rich solid propellant can be cast and cured to form defect - free propellant grain, ap grading and metal fuels changing including variety and addition amount have been adjusted and investigated. the result shows that, after the adjustment, all the slurries can be cast to obtain structural perfect propellant grain which may be used to test various propellant properties

    4 、為了使現有含硼推進劑的燃燒等性能進一步提高和改善，同時為了能使現有含硼推進劑藥漿澆鑄后得到結構完整性和均勻性更好的藥柱，在2 、 3研究的基礎上，對ap的級配、低燃點金屬燃燒劑的品種和加入量等進行了較深入的研究，結果表明：這些組分進行調節后的各藥漿的流平性變化均能滿足澆鑄要求，並製成能進行推進劑其它性能測試的小方坯。
  7. Our research found that, the main reason which led to the oscillation of jet and arc voltage was the oscillation of propellant flowrate. the oscillation of flowrate was caused by the oscillation of water evaporation in pipes

    本文的研究發現導致水電弧加熱發動機羽流和電壓脈動的主要原因為推進劑流量供給的脈動，而供給流量的脈動是由於水在管內汽化的脈動引起的。
  8. 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。
  9. The two - dimensional axisymmetric subsonic - transonic - supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method. the profiles of density, velocity, temperature, pressure and mach number can be obtained by the computation. the computation grid and some computed results are given here. the test equipment such as power supply system, ignition system, propellant supply system, arcjet thruster, thrust measuring device and vacuum system are introduced briefly. some working phenomena of the arcjet are observed and discussed. three different kinds of instability appeared in the process of the experiments. except some important parameters are measured, it is found that the operating stability of argon is better than that of nitrogen

    對一實驗電弧加熱式發動機二維軸對稱亞跨超音速流動進行了數值模擬，所採用的方法是矢通量分裂演算法.通過計算可以得出密度、速度、溫度、壓力和馬赫數的分佈.給出了計算所使用的網格和一些計算結果.簡要介紹了實驗所使用的設備，如電源系統、點火系統、推進劑供給系統、電弧加熱式發動機、推力測量裝置和真空系統.對所觀察到的一些工作現象進行了討論.有三種不同的不穩定性出現于實驗過程.除了所測量的一些重要參數，通過實驗發現氬比氮工作更穩定
  10. Laws are drawn, disadvantages are explained and solve is suggested. according to the conclusion of tests, changes are made toward the structure. lot ' s of tests are carried out under different conditions

    針對改進后的結構，本文在各不同推進劑質量流量、不同弧電流的工況之下進行了系統的性能測試，並將所得到的結果與改進前的結論進行了比較。
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