推進劑性能 的英文怎麼說

中文拼音 [tuījìnjìxìngnéng]
推進劑性能 英文
performance of propellant
  • 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...
  • 性 : Ⅰ名詞1 （性格） nature; character; disposition 2 （性能; 性質） property; quality 3 （性別） sex ...
  • 能 : 能名詞（姓氏） a surname
  • 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. Flame temperature measurements can be used as a guide in discussing energetics of a homogeneous propellant.

    火焰溫度的測定可作為討論均質推進劑能量特性的指導。
  2. 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。
  3. The reason of these improvements are discussed as a base of lower down the power level without the debasement of performance and the alter of propellant by hydrogen or hydrazine

    為今後進一步在確保性能的前提下降低發動機功率以及以氫氣、氮氣混合或者肼作為推進劑的電弧加熱發動機的探索和研製奠定了基礎。
  4. As the air - breathing engine, the performance of solid rocket ramjet is determined not only by structure of engine and the performance of propellant, but also by flight condition

    作為吸氣式發動機，其性能不僅取決于發動機本身結構和推進劑性能，與飛行狀態也有密切的聯系。
  5. The mechanical properties of improved double-base propellants enabled one to envisage grain geometrics with large combustion areas and consequently high thrusts.

    經過改進的雙基推進劑的機械性能使我們能夠指望獲得大燃燒面的藥柱幾何形狀，從而得到大推力。
  6. What the study of the software of configuration analysis of liquid propellant space propulsion systems solved is how to develop the software of configuration analysis of liquid propellant space propulsion systems using scientific software model based on the characteristics of liquid propellant space propulsion systems in order to improve the performance and reduce the mass etc. it ' s important that can save fees and improve corporation ' s ability of participating competition

    液體推進劑空間推進系統構型分析軟體研究所要解決的問題是如何根據液體推進劑空間推進系統的特點，通過運用科學的軟體模型開發液體推進劑空間推進系統構型分析軟體。其目的是為了提高推進系統性能、減少推進系統質量等。進行液體推進劑空間推進系統構型分析軟體研究對于節約國家經費、提高企業競爭力有著重要的意義。
  7. Explosives for civil uses - propellants and rocket propellants - part 7 : determination of properties of black powder

    民用炸藥.推進劑和火箭推進劑.第7部分:黑火藥性能的測定
  8. The experimental study on the thermal aging combustion property of the composite modified double base propellant and its life - time calculation

    改性雙基推進劑熱老化燃燒性能試驗研究與壽命預估
  9. 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。
  10. It is very difficult to research the burning characteristic of high energy propellant in the ddt pipe applying the ionization probe. but the satisfactory results can be easily got using photoelectricity triode

    用探針法研究ddt管中高能推進劑的燃燒波和爆轟波的傳播特性，因各種因素的影響難以得到滿意的結果，用光電三極體代替電離探針可得到相對理想的結果。
  11. 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。
  12. Explosives for civil uses - propellants and rocket propellants - part 7 : determination of properties of black powder ; german version en 13938 - 7 : 2004

    民用炸藥.推進劑和火箭推進劑.第7部分:黑火藥的性能
  13. However, solid propellant is viscoelastic and nearly - incompressible, and the material parameters and load process ca n ' t be given accurately in general

    固體推進劑具有粘彈性和近似不可壓縮性，其材料參數和外激勵過程通常不能精確給出。
  14. Energetic materials for defense. physico - chemical analysis and properties. graphite, carbon black, tin oxide of single and double base properlants

    國防用高能材料.物理-化學分析及特性.單基和雙基推進劑的石墨碳黑和氧化錫
  15. On the fundamental of thermo - viscoelasticity, the rate of viscous heat generation in csp matrix in relation with stress and strain status, is obtained. the meso - scale model is put forward, in which processes or phenomena such as viscous heat in csp matrix, heat conduction between csp matrix and oxidant particulates, decomposition of oxidant and its interfacial reactions with csp matrix, are described. the control equations are derived

    應用熱粘彈理論、傳熱學、推進劑熱分解動力學等，分析推導了推進劑粘性加熱與應力應變的關系，建立了描述基體粘性加熱、基體與含能顆粒傳熱、含能顆粒受熱分解及與基體界面反應等過程的細觀模型，推導建立了模型控制方程。
  16. 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
  17. The processing techniques to manufacture gap net polymer and gap fuel - rich propellant were determined by means of careful selections of curing parameter, proper curative and crosslinking agent, addition of stabilizer and etc. the mechanic property of gap propellant was modified by addition of chain extender. as a result, the gap fuel - rich propellant was developed. by means of dsc and pdta methods, the thermal decomposition characteristics of gap model fuel - rich propellant and its ingredients at both 0. 1 and 0. 5 mpa were investigated

    通過調節固化參數，選擇合適的固化劑和交聯劑體系，添加安定劑以及改進工藝步驟等方法，解決了gap預聚物及gap貧氧推進劑制備工藝中的關鍵技術；採用添加擴鏈劑的方法改善了gap貧氧推進劑的力學性能；最後研製出一個可實用的gap貧氧推進劑配方。
  18. 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。
  19. According to the change of the chemical properties and the mechanical properties obtained from the tests, the simulation of interior ballistic and the structural integrity analysis for these motors were conducted

    根據試驗測得的推進劑化學性能和力學性能的變化，對不同貯存期的發動機進行了內彈道和結構完整性計算。
  20. The experiment research of the energy characteristics of the solid propellant of the over - storage solid rocket motors

    超期貯存發動機固體推進劑能量特性試驗研究
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