氣動加熱 的英文怎麼說

中文拼音 [qìdòngjiārè]
氣動加熱 英文
aerodynamic heating
  • 氣 : Ⅰ名詞1 （氣體） gas 2 （空氣） air 3 （氣息） breath 4 （自然界冷熱陰晴等現象） weather 5 （氣味...
  1. Under the assumption that the inner surface of stator sleeve and outer surface of rotor are smooth, taking the fact into account that the temperature of stator sleeve of evaporation cooling motor keeps almost the same, horizontal evaporation cooling motor is simplified as a physical model of two coaxial sleeves, with outer sleeve ( the stator ) holds still and keep at constant temperature and inner sleeve ( the rotor ) is rotating and heated

    本文通過數值和實驗手段研究了臥式蒸發冷卻電機楔形氣隙中的流體流動、傳熱現象。本文在定子套筒和轉子表面光滑的假設下，針對蒸發冷卻電機定子套筒壁面基本恆溫的特點，將實際蒸發冷卻電機簡化為同軸套筒內筒加熱旋轉、外簡靜止定溫的物理模型。
  2. Our hot balloons is driven by common fuel without any gas, as same as other normal hot balloons, it is lifted by flotage of hot air and direction controlled by gasoline motor, remote operation, safe, low risk, no ground people required leading to very low cost

    本廠生產的動力熱氣球，是用普通熱氣球燃料，不加任何氣體，和普通的熱氣球一樣，是靠熱氣的浮力上升的，汽油機控制方向和升降，遙控操作，安全，風險小，無須地面人員，飛行成本底。
  3. Series of guowei dry - method composite machines as new product are explored with our many years ' experience, the requirement of the users. the first metal of this machine is adopted with : photo - ecectricity auto. tracking " correcting deviation equipment, magnetic powder tension control. pneumatic back pressure shifting blade, oven temperature controlled qutomatically, big roll with oil heating, coating composite pneumatic control as well as double frequency governor etc. it will make the machine with fast speed, lower voice, low polluted by air, shout consumptionfor energy, stable working etc. especially suitable for al - foil with smooth surface and no enough firming, glass paper, polyester ect. the composite material with hard strength, fireproof, anti - ventilation, anti - fatty, frozen, dudrable steam etc character. it is widely used in food, pharmacy, as well as daily articles to package

    「國偉」 、系列乾式復合機，是我廠根據多年的復合機製造經驗及結合客戶需求，開發的新產品，該機第一基材採用了「光電自動跟蹤」糾偏放卷裝置，磁粉張力控制、氣動背壓移動式刮刀、烘箱溫度分段自動控制、大輥筒導熱油加熱、上膠復合氣動控制及雙變頻調速技術，使該機具有復合速度快、噪聲低、空氣污染小、能耗低、運行平穩等特點，適宜於表面光滑的鋁箔玻璃紙聚酰胺等與聚乙烯、聚丙烯等薄膜的復合，復合薄膜具有強度高、防水、防透氣、防油脂、可冷凍、蒸煮等優點，廣泛應用冷凍食品、乾燥食品、醫藥品及日用品的包裝。
  4. The results indicate that : the high positioned air inflow do good to heat transfer in rotator disk ; different size of radial outflow have small effects on flow and heat transfer ; the heat transfer near rotating disk increases as rotating reynold number increases or non - dimensional mass flow rate increases

    結果表明，高位軸向進氣對轉盤換熱有利；不同的徑向出口大小對盤腔內的流動換熱影響不大；隨旋轉雷諾數和無量綱質量流量增加，轉盤盤面的換熱效果增強。
  5. The fifth chapter sum up the article and view the work. the simulation results indicate : ( 1 ) exchanging of sea - air and force of dynamical and thermodynamic processes is very important to bring and maintain sea surface wind. shf is mostly energy sources and lhf is negative effect in some area

    模擬結果充分表明： （ 1 ）感熱和潛熱的海氣交換和動量交換（摩擦作用）對于海面風的發展和維持起著重要作用，潛熱加熱是海面風中最主要的能源，感熱通量在一武漢理工大學碩士學位論文定區域對海面風風場有負面影響。
  6. The diagnostic analysis for the sandstorm process on the base of height, temperature, pressure and wind etc output from the model shows that the upper cold trough, low - level wind shear, surface cold anticyclonic ridge, mesoscale cyclone and cold front are the main synoptic systems, surface cold anticyclonic ridge and cold front provide condition of wind force to occurrence of the sandstorm weather, the strong mesoscale cyclone before front makes pressure gradient before and after cold front obviously strengthen, moreover, and it increases obviously the temperature of the controlled area, as a result, the updraft movement caused by convergence before front strengthens

    500hpa強鋒區、 700hpa切變和鋒前中尺度系統的強弱及位置變化是沙塵暴天氣發生發展到減弱的直接原因。地面冷高壓、地面氣旋及冷鋒是造成本次沙塵暴天氣的主要地面天氣系統。地面冷高壓及冷鋒為沙塵暴天氣的發生提供了風力條件，而中尺度氣旋使冷鋒前後氣壓梯度明顯增強外，又使所控制的區域增溫明顯，使鋒前輻合上升運動加強，為沙塵暴天氣的發生提供了熱、動力條件。
  7. The aerothermoelastic analysis of missile structure includes the thermal stiffness, thermal vibration and thermal flutter analysis. this dissertation emphasizes on thermal vibration analysis of the aerial vehicle under aerodynamic heat condition

    本文研究背景是彈體這類典型結構在高速飛行情況下，由於氣動加熱引起的高溫對結構氣動熱彈性分析，包括熱剛度、熱振動問題的研究。
  8. 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。
  9. Principal conclusions were drawn as the following : the non compatibility of pressure or velocity of the gas on both sides of the contact surface is the cause of the formation of shock wave ; the heating effect of reflective shock wave to driving gas during charging or exhausting process is the internal mechanism of peak oscillating effect, and all the factors that influence the formation and the running of the shock wave will influence the peak oscillating frequency, cooling effect

    主要結論如下：熱分離機內激波形成的原因是射氣瞬間接觸面兩側壓力和速度不相容；峰值振蕩效應的內在機制為反射激波對充氣階段的驅動氣或低溫排氣的加熱，凡是影響激波形成及運動的因素都將對峰值振蕩頻率、冷效應及熱效應產生影響；當充、排氣時間比為0 . 1763時，最佳射流激勵頻率出現在高階峰值振蕩頻率上。
  10. The return of a reusable spacevehicle into earth ' s atmosphere with high - supersonic is gas - heated intensely, which requiring the high performance of thermal protection provided by the hot - structure composite materials

    可重復使用空天飛行器以高超音速再入大氣層時受到強烈的氣動加熱，對結構的防熱性能提出了很高的要求。
  11. In the beginning of cold - start, the monolith is heated only by the gas ; after light - off, the monolith is heated by the heat released by the chemical reaction

    在冷起動初始階段，載體僅受排氣的加熱;當載體的溫度達到起燃溫度后，化學反應伴隨的放熱進一步加熱載體，使其溫度迅速上升。
  12. Oil fired forced convection air heaters - stationary and transportable for space heating

    燃油強制對流氣體加熱器.固定和可移動對流式空間加熱器
  13. Specification for dedicated liquefied petroleum gas appliances - mobile and portable non - domestic forced convection direct fired air heaters

    專用液化石油氣設施的規范.移動和便攜式非家用強制對流直燃式氣體加熱器
  14. In this paper, some methods are developed to solve the relative problems on thermal vibration of the elastic structure

    重點研究彈體結構的熱振動特性。在計算氣動加熱及熱振動方面，本論文提出了一些解決方法。
  15. Abstract : approximate methods for calculating aerodynamic heating rates on space shuttles are discussed. various methods are given for predicting the heating rate at axisymmetric stagnation points, general three dimensional stagnationpoints and the leading edge stagnation point of wings. numerous laminar and turbulent heating techniques for flat plates and cones are analyzed and compared. a brief review of some methods is presented to predict heating rate for winward centerline and lateral direction off the symmetry plane. the results show that the methods are simpler and can guarantee enought precision for predicting aerodynamic heating environment of space shuttles

    文摘:介紹了國內外預測航天飛機氣動加熱的工程計算方法.給出了軸對稱、非軸對稱和機翼前緣等各種外形駐點熱流密度的計算，分析和比較了平板、錐體的層流和湍流熱流密度計算的各種方法，概述了航天飛機迎風面中心線和離開中心線橫向熱流密度的計算.計算結果表明，本文方法用在航天飛機氣動熱環境初步設計中比較簡單並且有足夠精度
  16. Because these projectiles attain hypervelocity within the atmosphere and are subjected to enormous heating as well as aerodynamic loads, the survivability of the front region of projectile wing is very important for designer to consider

    由於這類彈丸在大氣中高速飛行，並受到劇烈的氣動加熱及空氣動力負荷的作用，因此，彈翼前緣部的生存能力就成為彈丸設計中必須要考慮的問題。
  17. Preferences of the main working parameters of the auto - heating system for constant temperature in biogas digester

    沼氣反應器中自動加熱恆溫系統主要工作部件的參數選擇
  18. Green " s theorem is employed to find the quantity relationship among the constraints of heating rate, dynamic pressure and lift in reentry flight. the paper deduced the approximate solution of the optimal aeroassisted coplanar trajectories under the three typical constraints. the performance index to be minimized are either heat input, the total dynamic pressure, time during the atmospheric flight, the time integral of the square of the path inclination ; or maximize the time of flight during the atmospheric portion of the trajetory. an important conclusion is firstly obtained : under the three constraints above, the optimal aeroassisted coplanar transfers with the first forth kinds payoffs have the same optimal control laws

    採用格林函數法，給出了同一平面氣動力輔助變軌飛行的3種過程約束（氣動加熱率、動壓、升力約束）條件之間關系的近似定量描述形成的飛行包絡線.由此求解了航天器同時受3種約束條件時，各種性能指標下的同一平面氣動力輔助變軌軌跡的近似解及相應的最優控制規律.文中對近似解與控制規律的內部結構作了細致的分析，得到了一些有益的結論
  19. Thirdly, this dissertation briefly introduces the engineering estimation method of the aerodynamic heat and supplies the simplified formulas. not considering the rejection, the ablation and some other factors, the author calculates the stagnation heat flux and the non - stagnation field heat flux distribution of some fly situation as the example aerodynamic heat environment. finally, by using the ansys program, the thermal vibration characters of the plate and missile body structures with different materials is analyzed

    這一方法提高了熱振動的分析效率；第三，簡要的介紹了工程上計算氣動熟的估算方法及熱流密度計算的簡化公式，在不考慮燒蝕以及質量引射等影響下，本文計算了幾種飛行條件下駐點和非駐點區的熱流密度分佈，作為本論文算例的氣動加熱環境。
  20. Aerodynamic heating simulation of terminal - sensitive submunitions in missile based on matlab

    的導彈末敏子彈氣動加熱模擬
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