推進劑點火 的英文怎麼說

中文拼音 [tuījìnjìdiǎnhuǒ]
推進劑點火 英文
propellant fire
  • 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...
  • 點 : Ⅰ名詞1 （液體的小滴） drop （of liquid） 2 （細小的痕跡） spot; dot; speck 3 （漢字的筆畫「、」）...
  • 火 : fire
  • 推進 : 1 （推動工作 使前進） push on; carry forward; advance; give impetus to 2 [軍事] move forward; dri...
  • 點火 : 1 （挑起是非） stir up trouble 2 （點燃; 打火） ignite; light the fire; fire up; strike a light; ...
  1. The comparison between the solid bipropellant firing results and the monopropellant firing results appears to be quite good.

    固體二元推進劑和單元推進劑的點火試驗結果是很相近的。
  2. 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。
  3. We shall try by means of a highly simplified development to expose certain advantages and disadvantages of solid propellant rocket systems.

    我們想通過相當簡單的推導來試圖闡明固體推進劑火箭系統的某些優缺點。
  4. The transportable powder series extinguishers are effective extinguishing appliances, in which extingshing agent sodium bicarbonate or ammonium phosphate powder together with the driving gas - nitrogen are filled in a full - sealed container. during application, nitrogen drives to jetting powder for extinguishing, which is advanced in technology, simple in structure, convenient in operation, maintenance and storage, safe and reliable

    推車式乾粉系列滅火器是一種新型高效的滅火器材，它使用磷酸銨鹽或碳酸氫鈉乾粉滅火劑和驅動氣體氮氣一起灌裝在全封閉的容器內，滅火時由氮氣驅動乾粉滅火劑噴射滅火，具有技術先進，結構簡單、操作方便、易於維修、便於保管，安全可靠等優點。
  5. 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。
  6. The paper firstly reviews the history and developments of the research and application on kinds of precooling methods recently adopted. then, the paper lays emphasis on the experimental investigation of natural circulation precooling

    本文首先介紹了低溫推進劑火箭發動機的各種預冷方法的研究和應用的歷史和現狀，然後重點對自然循環預冷法進行了實驗研究。
  7. The two - dimensional axisymmetric subsonic - transonic - supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method. the profiles of density, velocity, temperature, pressure and mach number can be obtained by the computation. the computation grid and some computed results are given here. the test equipment such as power supply system, ignition system, propellant supply system, arcjet thruster, thrust measuring device and vacuum system are introduced briefly. some working phenomena of the arcjet are observed and discussed. three different kinds of instability appeared in the process of the experiments. except some important parameters are measured, it is found that the operating stability of argon is better than that of nitrogen

    對一實驗電弧加熱式發動機二維軸對稱亞跨超音速流動進行了數值模擬，所採用的方法是矢通量分裂演算法.通過計算可以得出密度、速度、溫度、壓力和馬赫數的分佈.給出了計算所使用的網格和一些計算結果.簡要介紹了實驗所使用的設備，如電源系統、點火系統、推進劑供給系統、電弧加熱式發動機、推力測量裝置和真空系統.對所觀察到的一些工作現象進行了討論.有三種不同的不穩定性出現于實驗過程.除了所測量的一些重要參數，通過實驗發現氬比氮工作更穩定
  8. 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。
  9. 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。
  10. The test equipment such as power supply system, ignition system, propellant supply system, arcjet thruster, thrust measuring device and vacuum system are introduced briefly

    簡要介紹了實驗所使用的設備，如電源系統、點火系統、推進劑供給系統、電弧加熱式發動機、推力測量裝置和真空系統。
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