推進劑溫度 的英文怎麼說

中文拼音 [tuījìnjìwēndù]
推進劑溫度 英文
propellant temperature
  • 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...
  • 溫 : Ⅰ形容詞（不冷不熱） warm; lukewarm; hot; gentle; mild Ⅱ名詞1 （溫度） temperature 2 （瘟） acute ...
  • 度 : 度動詞[書面語] （推測; 估計） surmise; estimate
  • 推進 : 1 （推動工作 使前進） push on; carry forward; advance; give impetus to 2 [軍事] move forward; dri...
  • 溫度 : [物理學] temperature
  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. Based on physical simulation and numerical simulation, the conversion of hot water slug flooding with nitrogen foam is presented and some injection indices are optimized, including foam concentration, gas - liquid ratio, injection rate, temperature of water, slug length. from reservoir research and oilfield development, studying disadvantageous factors, the paper will have guilding value for heavy oil reservoir development of leng 43 block

    對熱水+氮氣泡沫段塞驅的關鍵技術指標，包括泡沫劑濃度、氣液比、注入速度、注水溫度和段塞長度等重要參數進行了優選，提出了注水速度80 100t d 、氣液比1 ： 1 、注水溫度95 100 、溶劑濃度0 . 5的推薦方案。
  4. Because modified arrhenius formula considers the effect of temperature variation to activation energy, by the proposed methods, propellant storage life can be predicted more accurately, compared with arrhenius method which considers activation energy as a constant

    由於修正的阿倫尼斯公式考慮了溫度變化對活化能的影響，所以與將活化能看成常數的阿倫尼斯方法相比，文中方法可以更準確地預測固體推進劑的貯存壽命。
  5. Furthermore, by integral method, all test data at different aging temperatures can be analyzed as an integration, so the prediction precision of storage life can be increased with the same specimens, or specimens can be saved in the same precision by this method

    而且，固體推進劑貯存壽命整體預測方法能將各個老化溫度下的固體推進劑試驗數據作為一個整體進行統計分析，具有更大的信息量，可以提高壽命預測精度或節省大量試樣。
  6. 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。
  7. 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。
  8. 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。
  9. 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
  10. It is concluded that increase of temperature in csp matrix is of great extent, and is in dependence with impact velocity, rate of deformation and thermorheologic

    分析計算表明:撞擊變形條件下粘性加熱使推進劑基體溫度顯著上升，溫度升幅與撞擊速度、剪切變形、推進劑熱流變特性密切相關。
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