氣動力風洞 的英文怎麼說

中文拼音 [qìdònglìfēngdòng]
氣動力風洞 英文
aerodynamic tunnel
  • 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...
  • 力 : Ⅰ名1 （力量; 能力） power; strength; ability; capacity 2 [物理學] （改變物體運動狀態的作用） forc...
  • 風 : Ⅰ名詞1 （空氣流動） wind 2 （風氣; 風俗） practice; atmosphere; custom 3 （景象） scene; view 4 ...
  • 洞 : Ⅰ名詞（物體上穿通的或凹入較深的部分; 窟窿; 洞穴） hole; cavity Ⅱ形容詞（深遠; 透徹） profound; thorough; clear
  • 風洞 : [航空] wind tunnel; air tunnel; whirl tube; wind tunnel plant; flume
  1. This paper adopts linear interpolation to deal with data of wind tunnel experiment for sample uav and realizes modeling and simulation of the sample uav with c language in common aerodynamics and moment coefficient

    本文採用線性插值處理樣例無人機風洞試驗數據，採用正常情況下的氣動力及力矩系數數學模型，並用c語言實現樣例無人機建模與模擬。
  2. Fluid experiment ; buff body aerodynamics ; wind engineering ; wind loading on buildings and structures ; modeling wind in an atmospheric boundary wind tunnel ; pedestrian - level wind environment ; wind effects on the efficiency of air - cooled condenser in a large power plant

    實驗流體力學，鈍體空氣動力學，風工程， 、建築物和結構物的風荷載研究，大氣邊界層風洞模擬，行人高度風環境，大型電站空冷系統風效應風洞模擬。
  3. As to the current problems existing in the identification for these flutter derivatives, the dissertation tries to trace the development in the identification for the past unsteady aerodynamic forces of long - span bridges. it also investigates the method for flutter and buffeting analysis and the flutter derivatives. based on the present methods used in obtaining the unsteady aerodynamic forces and flutter derivatives, and co - funded by a natural scientific fund from the nation and a key project fund from the railway ministry, the current research has attempted to develop a device which can be employed in the wind tunnel to test flutter derivative through a forced vibration method

    鑒于目前橋梁斷面顫振導數識別的水平和存在的問題，本文通過對大跨度橋梁非定常氣動力、顫振分析方法及顫振導數識別方法的回顧和評述，基於現有的非定常氣動力和顫振導數的測試方法，在國家自然科學基金與鐵道部重點學科基金的聯合資助下，研究開發了一套在風洞中採用強迫振動法測試顫振導數的裝置。
  4. According to the requirements of propeller aerocraft model test in wind tunnel, specifications of the driven motor is presented by aerodynamic analysis, and a short - term operated high power density three - phase induction motor is developed with reasonably designing the motor, such as electromagnetism load, heat checkout and high - efficiency heat exchanger

    摘要針對螺旋槳飛機模型帶動力風洞實驗要求，通過氣動性能分析提出驅動電機的技術指標，在滿足結構約束的條件下，通過合理設計電機的電磁負荷、校核發熱、採用高效冷卻裝置等，研製出短時工作制高功率密度三相異步電機。
  5. The balance, which is widely applied in aviation, astronautics, architecture, high - speed engines and weapon ' s manufacture, is the professional testing equipment in aerodynamic experiment

    應變天平是風洞空氣動力學實驗中的專用測試裝置，被廣泛應用於航空、航天、建築、高速機車以及武器研製等領域。
  6. An efficient wind field simulation technique for wind - induced vibration analysis of long - span bridges is first introduced in this paper ， and the statistic characteristics of the simulated wind field are then discussed on this basis ， the time - domain expressions for the buffeting and self - excited forces acting on long - span bridges are further given a simple and practical method is presented for the non - linear parameter identification involved in the calculation of self - excited forces by using the above theory ， the wind field and aerodynamic forces acting on the hong kong ting kau bridge are obtained the time - domain buffeting response analysis of the bridge shows that the analytic results agree quite well with the experimental ones this indicates that the theory presented in this paper has reached a practical level

    介紹了一種快速高效的用於大跨度橋梁風致振動分析的風場模擬方法，並對模擬風場的統計性質進行了討論和驗證在此基礎上進一步給出了大跨度橋梁抖振力和自激力的時域表達方式，其中針對自激力計算中涉及的參數識別問題，提出了一種簡單實用的非線性參數識別方法本文採用上述理論，獲得了作用於香港汀九大橋上的風場和氣動力，據此對大橋進行的抖振響應時域分析表明，計算結果與風洞試驗結果吻合良好，說明文中述及的這套理論已達到實用的階段
  7. In this paper i was in virtue of the fluent software, set up the geometrical model of jin ’ ao mansion and adjacent buildings, used non - equilibrium wall functions to deal with the problem which come from the near wall, used realizable k - turbulent model to simulate the steady flow around 3d high - rise buildings, we can get the distribution of mean wind pressure coefficient of the surface of jin ’ ao mansion and five aerodynamics components. they were compared with the data from the wind tunnel test, we found out the distance between the result of the wind tunnel test and numerical simulation in the acceptable range

    本文以fluent軟體為平臺，建立金奧大廈及其周邊建築的計算幾何模型，近壁區採用非平衡壁面函數法處理，運用基於雷諾時均的realizablek -湍流模型進行高層建築三維定常風場數值模擬，獲得金奧大廈表面時均風壓系數分佈及基底五分量氣動力，並和風洞測壓試驗的結果及風壓系數積分計算的基底五分量氣動力相比較，發現兩者之間的差異在可接受的范圍之內。
  8. This paper presents the development and preliminary application works of an automatic strain gauge balance static calibration system in ecs for 1m hypersonic wind tunnel of cardc

    本文論述了cardc超高速空氣動力研究所1m高超聲速風洞配套的新型全自動六分量應變天平地軸系（ ecs ）校準系統的研製和初步應用研究工作。
  9. According to the study work of this paper, an automatic six - component strain gauge balance calibration system development scheme was put forwards : the system calibrates the balances in the ecs, and translates the loads to the bcs of the balances with measuring the balance ’ s position changes during the calibration

    本文根據1m高超聲速風洞氣動力試驗的總體要求，提出了採用天平校準載荷地軸系全自動加載、並通過天平空間位移測量將校準載荷換算到天平體軸系（ bcs ）的六分量天平校準系統總體研製方案，並確定了詳細的技術指標。
  10. Wind tunnel strain - gauge balance is the most popular measuring device in the aerodynamic force - measuring test in the wind tunnels, and the performance of the balance would effects the tests results on accuracy

    風洞應變天平，是目前國內外各類型風洞在氣動力測量試驗中廣泛採用的測量裝置，其性能指標直接影響測力試驗數據的精準度。
  11. By acquiring the structure and environment parameters, the active control can greatly reduce the vibration on the model and the supporters caused by the unsteady aerodynamic force which badly influences the experienced data precision

    在進行風洞試驗時，受非定常氣動力的作用，模型會與天平、支桿和支架一起產生振動。模型劇烈的振動嚴重影響風洞測力試驗數據的精度。
  12. Abstract : based onmethods of foreign countries of using wi nd tunnel test and numerical flow simulation, optimum nose a nd tail shapes ofhigh - speed trains are studied to achieve optimum aerodynamic performance so as to efficiently reduce the influence of theaerodynamic phenome na on the train operation and the environment. research results of foreign countr ies are introduced

    文摘:針對國外利用以風洞模型模擬試驗和以流場數值模擬計算為主的方法來尋求高速列車最佳的頭尾部形狀，使列車的綜合氣動性能最佳，從而有效地降低空氣動力學現象對列車運行和周圍環境的影響進行了探討，介紹了國外在此方面取得的主要成果。
  13. These landslides go with fluidization peculiarity different degree in course of their motion, and their speed and distance increase several times because of the fiuidization, thereby the disaster area greatly broaden. on the base of above, the paper studies systematically the fluidization of large high - speed rockslides in all its aspects : analyzed the aerodynamic effect in the short - range on the base of the wind turmel experiment, studied the effect of falling into pieces when landslides collides mountain ; studied the accelerating effect through high - speed collide experiment of landslides model ; and the paper reappear the overall process including set - out, collide in the short range, debris flow in the long - range of touzhai large landslide via distinct element method ( dem ), studied the flow law and equation of different type of debris flow resulted from large landslide. as a sample to apply, the paper analyzed fluidization mechanism of touzhai landslide

    基於這一點，本文對大型高速巖質滑坡的流體化現象進行了全面而系統的研究：通過風洞模型實驗，研究了大型高速滑坡凌空飛行階段的空氣動力學效應，研究了飛行中滑坡巖體在與途中不動山體發塵碰撞時的解體破碎效應，通過滑坡巖體高速碰撞模型實驗研究了滑坡巖體解體破碎後部分巖體的加速運動效應，並應用離散單元法再現了雲南頭寨溝大型滑坡啟動高速、近程碰撞、遠程碎屑流運動的全過程，研究了巖體解體破碎后形成不同類型碎屑流的運動規律及運動方程，並對頭寨滑坡流體化運動機理進行了實例分析，取得了以下主要結論和成果： （ 1 ）對于大型高速滑坡，大多在啟程活動階段已獲得了高速，這使得這類滑坡在其離開剪出口之後以凌空飛行的形式向前運動，在其飛行過程中，滑坡巖體與空氣強烈作用，並產生空氣動力學效應，滑坡巖體在因碰撞而產生的解體破碎效應及部分巖體的加速運動效應的作用下，在遠程活動階段，以高速碎屑流的形式向前運動。
  14. An experimental study on the aerodynamic characteristics of new concept car is conducted by model wind tunnel test, covering the pressure coefficient and wake vortices on longitudinal symmetry plane, as well as aerodynamic forces and moments under different yaw angles

    摘要用模型風洞對新概念車在不同橫擺角下縱對稱面上壓力系數、整車氣動力和氣動力矩的變化以及縱對稱面尾部流態分佈進行了試驗研究。
  15. 2. the model experiment aimed at the aerodynamic effect of large high - speed landslides has been accomplished in wind tunnel laboratory for the first time. on the base of testing research, the paper studies different factor which influence the aerodynaxnic effect of flying 1andslide, and numerically simulates the aerodynamic effect with the help of the hydrodynamics finite element

    （ 2 ）首次在風洞實驗室進行了針對大型高速滑坡凌空飛行階段空氣動力學效應的模型實驗，研究了影響飛行滑坡巖體空氣動力學效應的不同因素；應用流體力學有限單元法對飛行滑坡巖體的空氣動力學效應進行了數值模擬。
  16. For testing, a partial - scale model of a tested automobile is placed in a wind tunnel to get the airflow pattern around the automobile. this is a traditional method and very expensive

    試驗主要是進行風洞試驗，它是汽車空氣動力學研究的主要手段，它是發現和驗證理論和計算方法的重要手段和基礎。
  17. In the paper, the computational results of all models are obtained, including 3 - d velocity field, 3 - d pressure field, and six aerodynamic coefficients. the results have good agreement with wind tunnel test

    文中得出了客車外圍流場的速度矢量圖和壓力分布圖以及六個氣動力系數，並將最終結果與風洞試驗結果進行了比較，結果吻合較好。
  18. Aerodynamic parameters measurement and flow visualization can be realized in this tunnel

    該風洞可以完成氣動力、氣動熱、壓力分佈的測量，以及流動顯示與測量。
  19. Wind tunnel test, as the one of general means of aerodynamic research, is very important and high effective

    風洞實驗作為空氣動力學研究的基本手段之一，是非常重要的，也是非常有效的。
  20. First, being based upon kalman filter, extended kalman filter formulas was established ; second, with using extended kalman filter in non - linear dynamics system maximum likelihood identification method, the self - contained formulas of estimating parameter was established ; third, according to the air layout of the missle, the aerodynamic parameters identification calculating model was gained, with applying to the non - linear dynamics system maximum likelihood identification method ; finally, with using the calculating model, the aerodynamic parameters were gained. the results which were gained from the calulating model were almost consistent with which were gained from the wind tunnel experiment. thus, it was viable to use the method to estimate the aerodynamic parameters

    首先，以卡爾曼濾波為基礎，將其推廣于非線性動力學系統，建立了廣義卡爾曼濾波算式；其次，把廣義卡爾曼濾波算式應用於非線性動力學系統最大似然演算法和非線性動力學系統最大似然遞推演算法中，建立了各自的參數估計完備算式；再其次，以所建立的傾斜穩定導彈空間運動數學模型為基礎，根據該導彈的氣動布局，推導並建立了該導彈空間運動數學模型，將最大似然遞推演算法應用其中，建立了導彈氣動力參數辨識的數學模型；最後，利用該模型，估算出了氣動力參數，所得結果與風洞實驗數據基本吻合，從而認為採用此方法是可行的。
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