推進劑室 的英文怎麼說
中文拼音 [tuījìnjìshì]
推進劑室
英文
propellant office propellant office-
Swelling and porosity of the propellant mixture became evident after 6 days at ambient temperature.
在室溫下放置6天後，推進劑混合物呈現膨脹和氣孔。One study used an eight-foot diameter toroidal combustor, burning liquid oxygen and gaseous hydrogen, with four different injectors.
有一項研究採用8英尺直徑的環形燃燒室用四種不同的噴注器，推進劑是液氧和氣氫。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。To appreciate the unsteady environment existing in liquid propellant rocket chambers it is necessary that the steady state be well understood.
為了分析液體推進劑火箭發動機燃燒室中存在的非穩態環境，必須很好地了解穩態狀態。The results indicate that with the coefficient of residual oxygen being less than 1 or around 1, when the fuel is injected into the combustor at the same combustor pressure, the higher the combustor temperature is, the less the coefficient of residual oxygen is when auto - ignition occurs ; when the fuel is injected into the combustor at the same combustor temperature, the larger the combustor pressure is, the less the coefficient of residual oxygen is when auto - ignition occurs ; when the fuel is injected into the combustor at the same combustor temperature and pressure, the bigger the coefficient of residual oxygen is, the more easily auto - ignition occurs
研究結果表明，當推進劑處于余氧系數小於1或略大於1時，在燃燒室壓力相同的情況下噴入燃料，燃燒室溫度越高，可自燃的余氧系數越小;在燃燒室溫度大致相同的情況下噴入燃料，燃燒室壓力越高，可自燃的余氧系數越小;在燃燒室溫度、壓力大致相同的情況下噴入燃料，余氧系數越高，自燃發生的可能性越大。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。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。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。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。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。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。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。分享友人