推進劑組分 的英文怎麼說

中文拼音 [tuījìnjìzǔfēn]
推進劑組分 英文
propellant inhibition
  • 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...
  • 組 : Ⅰ名詞1 （由不多的人員組成的單位） group 2 （姓氏） a surname Ⅱ動詞（組織） organize; form Ⅲ量詞（...
  • 分 : 分Ⅰ名詞1. （成分） component 2. （職責和權利的限度） what is within one's duty or rights Ⅱ同 「份」Ⅲ動詞[書面語] （料想） judge
  • 推進 : 1 （推動工作 使前進） push on; carry forward; advance; give impetus to 2 [軍事] move forward; dri...
  1. Abstract : to review the progress in the major ass ignment, the organization and implementation of protection against liquid rocket propellent

    文摘:綜述了發射大型運載火箭推進劑作業衛勤保障主要任務、保障重點、衛勤力量的分配、衛勤保障的組織和實施進展。
  2. 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。
  3. It is the fist thing to make particles to mix with htpb equally by the mixer. many superfine particles with various particle diameters, varieties, content and surface coated had been employed to study the influence on viscosity and dispersion of the slurry

    為了使加入的粉體通過捏合機的捏合，在丁羥膠中得到均勻的分散，我們分別研究了粉體的粒度、品種、組成及粉體表面經包覆處理后，對推進劑漿料的粘度、分散性的影響。
  4. Especially, when - bi together with a little carbon black ( cb ) or copper salt is used, the catalytic effect is better ; the flame structures of the double - base propellants containing - bi are similar to the typical plateau double - base propellant, but the combustion temperature distribution has been changed because of adding the - bi ; and the active components of catalysts deposit on the burning surface of propellants and the quenched surfaces of propellants with various catalysts possess different structure

    它與銅鹽和少量炭黑（ cb ）復合后，催化效果更優； 2 ， 4 -二羥基苯甲酸鉍加入后，推進劑的火焰結構保持了典型平臺雙基推進劑的結構特徵，但改變了雙基推進劑燃燒波溫度分佈，炭黑和銅鹽的加入對2 ， 4 -二羥基苯甲酸鉍的催化作用有很大影響；催化劑分解的活性組分富集在燃燒表面，不同催化劑使推進劑熄火表面形成不同的結構。
  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. Abstract : six quasi - ternary liquid - liquid equilibria systems between benzene, toluene, p - xylene, n - heptane, methyl - cyclohexane and n - formylmorpholine ( nfm ) + water have been determined at normal pressure and 60 ; the conjugate phase compositions and the contribution curves of these quasi - ternary liquid - liquid equilibria systems were obtained ; the experimental data were correlated using uniquac and nrtl models ; the plait points of these systems were obtained by the constructive fitting for the conjugate phase and parameter predicting methods ; the selectivity and contribution coefficients of the solvent to the solutes were calculated

    文摘:用液液平衡釜測定了常壓， 60下加水n -甲酰嗎啉和苯、甲苯、對二甲苯、正庚烷、甲基環己烷組分間6個擬三元體系的液液平衡，得到了擬三元液液平衡體系的共軛相組成和分配曲線；實驗數據用uniquac和nrtl模型進行了關聯；用共軛相作圖擬合法和模型參數推演算法獲得了各體系的褶點數據；並求得了溶劑對溶質的選擇性和分配系數。
  8. The results showed that the environmental pressure and catalysts have various actions on the thermal decomposition characteristics of the propellant and its ingredients. the burning rates of the gap / tmo fuel - rich propellants were measured by use of the pipe - connected unchoked ducted rocket testing facility

    實驗結果表明，在不同壓強下，貧氧推進劑各組分的熱分解特徵有所不同；在同一壓強下， tmo催化劑對貧氧推進劑中不同組分的催化作用不盡相同；同一催化劑，在不同壓強下對同一組分的催化能力也不同。
  9. On adjusting function components for optimizing rheological properties of slurry of boron - based fuel - rich solid propellant

    功能組分對含硼富燃固體推進劑藥漿流變特性的影響
  10. The present paper summaries the origin of the infrared radiant coating, the constituents of matrix of the radiant powder and the carrier adhesive, as well as the process of development and application of the infrared radiant coating, and analyzes factors affecting an extensive utilization of the material and discusses the application prospect and trend of development

    對紅外輻射塗料的起源、輻射粉體基料的組成、載體粘結劑的組成、塗料的應用與發展過程進行了綜述，分析了影響紅外輻射塗料推廣應用的原因，探討了其應用前景和發展趨勢。
  11. 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。
  12. Solid rocket motor ( srm ) grain is casted integrally from solid propellants. it is one of the important structural components and also provides fuels for srm. the reliability of srm grain should be paid great attention

    固體火箭發動機藥柱是由固體推進劑整體澆鑄而成的，既為發動機提供燃料，又是重要的結構組成部分，其安全性不容忽視。
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