推進劑燃燒 的英文怎麼說

中文拼音 [tuījìnjìránshāo]
推進劑燃燒 英文
propellant burning
  • 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...
  • 燃 : 動詞1. （燃燒） burn 2. （引火點著） ignite; light
  • 燒 : Ⅰ動詞1 （使東西著火） burn 2 （加熱或接觸某些化學藥品、放射性物質等使物體起變化） cook; bake; hea...
  • 推進 : 1 （推動工作 使前進） push on; carry forward; advance; give impetus to 2 [軍事] move forward; dri...
  • 燃燒 : （物質劇烈氧化而發光、發熱; 燒） burn; kindle; flame; set on fire; [化學] combustion; inflammation; ignition
  1. For proper combustion it is necessary to atomize the propellants.

    為了有效地進行燃燒，推進劑必須霧化。
  2. Study of deflagration - to - detonation transition of combustible gas

    高能推進劑燃燒轉爆轟的實驗和數值研究
  3. Deflagration - to - detonation transition in porous propel lants and cast propellants

    多孔和鑄裝高能推進劑的燃燒轉爆轟
  4. Numerical simulation of deflagration - to - detonation transition in high energy propellant

    高能固體推進劑燃燒轉爆轟的數值模擬
  5. 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。
  6. The above discussion on first-stage propellant slosh effects is based on the saturn vehicles, which use kerosene for fuel and lox for oxidizer.

    上面對于第一級推進劑晃動影響的討論，是建立在「土星」飛行器的基礎上，它是採用煤油做燃燒劑，液氧做氧化劑。
  7. In using eq. 3-1 of course one first identifies the fuel molecules and the oxidizer molecules of the propellant.

    當然，應用式（3-1）時首先要辨明推進劑的燃燒分子及氧化劑分子。
  8. 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。
  9. The time lag can be envisioned as the time required for the liquid propellants to travel from the injector to an effective combustion "front. "

    可以把遲滯想象為液體推進劑從噴注器運行到有效燃燒「鋒」所需的時間。
  10. 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。
  11. Because the propellant grain is viscoelastic material, the liner and adiabatic layer are also viscoelastic one, the interface debond problem is actually interface crack about elastic - viscoelastic or bi - viscoelastic materials. research about this problem relates to the knowledge of viscoelastic mechanics and interface fracture and combustion. numerical analysis method about interface debond on solid rocket motor is researched in this paper

    由於固體火箭發動機的推進劑藥柱是一種粘彈性材料，襯層和絕熱層也具有粘彈性性質，因此其界面脫粘問題實際上是彈性-粘彈性或雙粘彈性各向同性材料界面裂紋問題，對該問題的研究涉及到粘彈性力學、界面斷裂力學和燃燒學等相關學科。
  12. 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。
  13. 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。
  14. Closed burner method is used for determining burning rate of the solid propellants

    密閉燃燒器法是一種間接測定固體推進劑燃速的方法。
  15. The simulations results show that the spoiler is available to make the fuel and the oxidizer coming from the former to stay in the cavity for a long time, to let the fuel and oxidizer mix and burn completely. since there is a high temperature zone forming by vortex in the middle of the motor, it required a restricted thermal protection. the plate with holes decreased the vortex function in the cavity, which could not promote the combustion efficiency, but to decrease temperature in the cavity and be benefit to thermal protection of the wall

    計算結果分析表明:擾流板可以使燃料和氧化劑在擾流腔內的滯留時間加長，促進燃料與氧化劑的摻混燃燒，提高燃燒效率，但由於渦流在發動機的中間部位形成了高溫燃燒區域，致使局部燃料和絕熱層燒蝕速率增大，加大了熱防護的難度;孔板結構減弱了擾流腔內迴流區的漩流作用，不能增加推進劑燃燒效率，但可以使擾流腔內的溫度降低，給壁面熱防護帶來好處。
  16. Level set method was used in this paper to attain burning surface variety regulation of arbitrary configuration grain by tracing interface of grain surface burnback. the work of this thesis can be summaried as follow : 1

    本文運用等值面函數法（ levelset ） ，追蹤固體推進劑燃燒界面的變化，從而獲得了任意結構型面裝藥的燃面變化規律，本文的主要工作及創新點概括如下： 1
  17. In order to investigate the effect of 2, 4 - dihydroxylbenzoate ( - bi ) on the combustion of double - base propellant, the combustion law of the propellants containing - bi was studied by means of the single frame amplification photography fl miniature thermocouple, the scanning electron microscopy ( sem ) and the link isis energy spectrum

    摘要為了探索2 ， 4 -二羥基苯甲酸鉍對雙基推進劑燃燒的催化作用，採用單幅放大彩色攝影法、型微熱電偶技術、掃描電鏡和電子能譜研究了含2 ， 4 -二羥基苯甲酸鉍雙基推進劑的燃燒規律。
  18. The chemical reactions in the flame area are very complex. it is very difficult to measure the number density distribution of the particles ( atoms, ions and molecules ), so the relative intensity method is employed

    由於固體推進劑燃燒區內發生的化學反應非常復雜，直接測量火焰區內的粒子（原子、離子以及分子等）數密度比較困難，因此選用相對強度法來進行計算。
  19. This deduction forms the basis of the two-temperature postulate for composite propellant combustion.

    這種推理就是構成復合推進劑燃燒中兩溫概念的基礎。
  20. Liquid propellant combustion processes are quite complicated and defy precise analytical description.

    液體推進劑燃燒過程是相當復雜的，很難對其進行嚴謹的分析描述。
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