propellant gas 中文意思是什麼

propellant gas 解釋
氣體推進劑
  • propellant : n. 推進物，推進劑；（槍炮的）發射火藥；噴氣燃料。 high-energy propellant 高能燃料。 work horse propellant 【火箭】通用燃料。
  • gas : n （pl gases ）1 氣，氣體，氣態 〈cf fluid; solid〉 2 可燃氣，煤氣，沼氣；【礦物】瓦斯。3 【軍事...
  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. In this paper, simple reacting flow model in solid - propellant ducted rocket combustor based on eddy break - up model is established. the model is used to simulate the three - dimensional combustion flowfields in an experimental motor. some factors how to affect the combustion efficiency are discussed in the paper, including air intake and gas generator nozzle

    本文基於簡單反應的旋渦分裂模型，建立了固體火箭沖壓發動機補燃室內的湍流燃燒模型，並在該模型下對某實驗發動機進行了三維數值模擬，研究了補燃室設計參數包括進氣道出口設計參數和燃氣發生器噴管設計參數對燃燒效率的影響。
  3. When propellant is used in weapons with larger gas expanding ratio, the power capability accords with potential energy, and the power capability accords with impetus when gas expanding ratio is small

    發射藥在氣體膨脹比大的武器上應用時，做功能力與潛能較為一致；在氣體膨脹比小的武器上應用時，做功能力與火藥力較為一致。
  4. The results show that the thermodynamic properties of propellant combustion gas products have an important effect on its expanding power, and the correlation between conventional energy parameters such as impetus, potential energy and its power capability is not identical

    結果表明，發射藥燃氣產物的熱力學性質對其膨脹做功具有較大的影響，傳統的火藥力或潛能能量參數與做功能力之間的關系並非完全一致。
  5. A method of propellant charge techniqueto control the gas generation rate

    控制發射裝藥燃氣生成規律的一種方法
  6. The breakdown process of propellant gas was studied, calculation method of breakdown threshold value was obtained, the breakdown threshold value of hydrogen and air were calculated ; the inverse bremsstrahlung absorption process was studied, calculation method of inverse bremsstrahlung absorption coefficient of hydrogen and argon were calculated

    分析了激光對工質的去穿遷程，得到了去穿閾值的計算方法，計算了激光對空氣和氫氣的擊穿閾值；對工質中激光的逆初韌致吸收過程進行了研究，推導了逆韌致吸收系數的計算公式。
  7. In order to evaluate energy parameters of propellant accurately and impersonally, thermodynamic parameters of different propellant formulations were computed by potential energy method, and the correlations between the thermodynamic parameters and expanding power capability of propellant combustion gas in barrel weapon were researched

    摘要為了更加準確和客觀地評價發射藥的能量參數，採用內能法計算了不同組分發射藥配方的熱力學參數，研究了發射藥燃燒氣體在身管武器中的膨脹做功能力與熱力學參數的相互關系。
  8. The gap fuel - rich propellant showed short ignition delay time, high burning rate, and sensitive to variation of gas generator pressure. the results also showed that some tmo, such as moo3 and 0203 can increase the burning rate of the gap fuel - rich propellant

    測試結果表明， gap貧氧推進劑具有點火延遲期短、燃速高、燃速對壓強敏感性強等優點，且某些tmo催化劑如moo _ 3 、 co _ 2o _ 3等可顯著提高gap貧氧推進劑的燃速。
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