氣動力系數 的英文怎麼說

中文拼音 [qìdònglìxìshǔ]
氣動力系數 英文
aerodynamic coefficient
  • 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...
  • 系 : 系動詞（打結; 扣） tie; fasten; do up; button up
  • 數 : 數副詞（屢次） frequently; repeatedly
  • 系數 : [數學] coefficient; ratio; modulus; quotient; factor
  1. These effects appear to be negligible with respect to aerodynamic coefficients.

    就空氣動力系數這方面來說，這些影響似乎可以略去。
  2. The dynamic performance of a ram air system will vary with mach number and altitude and this tends to follow the aerodynamic characteristics of the missile.

    像導彈空氣動力特性一樣，沖壓空氣式系統的動態特性隨馬赫數和高度的變化而變化。
  3. 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。
  4. The aerodynamic characteristics of a projectile with wrap around fins are studied systematically in this paper, as follows : 1. the lift coefficients 、 drag force coefficients 、 pitch moment coefficients 、 pitch damping moment derivatives and roll damping moment derivatives are obtained from engineering calculation through looking wrap around fins as flat fins of the same projection aera

    本文對某卷弧尾翼彈氣動特性進行了系統研究，主要內容與結論為: 1 .將卷弧翼按照相同投影面積的平板翼進行工程估算，得到升力系數、阻力系數、俯仰力矩系數、俯仰阻尼導數、滾轉阻尼導數曲線。
  5. Three dimensional interaction flowfield over high - speed spinning projectile with lateral jets is numerically simulated in this dissertation firstly. complicated shocks wave patterns is analyzed. several factors concerned such as high - speed spinning, attack angle, base bleed and so on, are studied

    本文首次完成了高速旋轉彈丸側噴三維干擾湍流流場的數值模擬，分析了彈丸側噴流場復雜的波系結構，研究了高速旋轉、攻角、底噴等因素對彈丸側噴流場的影響規律，深入分析了旋轉側噴彈丸的空氣動力學特性。
  6. Several icing parameters were imported to calculate the change of drag coefficient and typical derivatives between clean aircraft and iced aircraft, and the aircraft flight envelope change of iced and un - iced situation was computed, and the small disturbance flight dynamics model was modified to study the effect of the ice accretion on the aircraft dynamics by importing the ice parameter to it, and the longitudinal and lateral stability and the elevator, aileron and rudder step response were also studied and simulated

    根據這些參數計算了飛機結冰后阻力系數以及典型氣動導數的變化，並計算了結冰前後飛機的飛行包線；同時對結冰前後飛機的縱向、橫側動穩定性以及升降舵、副翼和方向舵階躍操縱響應進行模擬計算。
  7. ( 2 ) on the leading edge, the film cooling effectiveness at the zone immediately downstream of the cooling holes is affected by blowing ratio and mainstream reynolds number, while the effects are not important in the downstream zone far from the cooling holes. ( 3 ) on the front half of pressure surface, the effectiveness increases with decreasing blowing ratio at the downstream near the cooling row and it is contrary at the downstream far from the cooling row. ( 4 ) on the rear pare of the pressure surface, the effectiveness decreases with increasing blowing ratio and does not vary so much downstream in the cases of higher blowing ratio

    研究結果表明葉片吸力面端壁附近區域壓力系數分佈呈現出較強的三維特性，動葉吸力面尤其明顯；氣膜孔流量系數隨吹風比的增加而增大，在高吹風比情況下，流量系數逐漸趨于常數；在不同型面區域，冷卻效率分佈有較大的差異，而且吹風比與主流雷諾數的影響程度也不盡相同；低吹風比下，孔出口下游附近可以得到較好的冷卻，中、高吹風比下，冷氣射流在加速流動主流的作用下返回壁面進行二次冷卻，孔下游較遠區域可以得到較好的冷氣覆蓋。
  8. Of all the aerodynamic parameters required in stability and control analysis, the hinge-moment coefficients are most difficult to determine with precision.

    進行穩定性和操縱性分析所需要的全部空氣動力參數中，鉸鏈力矩系數最難準確地確定。
  9. The complicated aerodynamics characteristic of spinning projectile with lateral jets and with attack angle is studied detailedly. the formation and changes are analyzed including magnus force, normal force, yawing moment, pitching moment and pressure center

    系統分析了旋轉側噴彈丸復雜的空氣動力學特性，分析了馬格努斯力系數、法向力系數、偏航力矩系數、俯仰力矩系數和壓力中心等參數的產生機理和變化規律。
  10. Computational fluid dynamics ( cfd ) techniques are used to study and understand fluid behavior in tunnels. by simulating complex specific operational cases, we can educe velocity or flux distribution in tunnel under different ventilation and resistance situation and determine the favorable operational procedures of the erlang mountain tunnel ventilation in a fire case. comparison has been made between a simulation and experiment for some cases in order to prove the cfd model is powerful, so that enables the study of cases for which experimental data is not available

    採用本文將隧道內的氣流看成是理想流體的一維恆定流動，通過對二郎山特長公路隧道半橫向通風系統建立隧道內的空氣動力學模型，利用計算機進行數值分析與計算，得出發生火災時，不同通風阻力條件下隧道中的風速分佈及流量分佈，並通過實驗室隧道模型實驗進行驗證與修正，依據研究結果給出了二郎山半橫向通風隧道的火災控制方案，從而解決了二郎山公路隧道通風對火災的控制問題，同時為半橫向通風公路隧道的火災通風提供科學的方法。
  11. Manufacturers and distributors of liquid and dry component process equipment for coatings, adhesives, and chemical products industries. focus is particle analysis, milling, vessel washing, and vapour recovery

    -產品有系列空氣錘電液錘整機電液錘動力頭數控全液壓模鍛錘鍛造操作機閉式單點壓力機多工位自動鍛造壓力機等。
  12. The second chapter simply introduces the development of alternate asynchronous inverter technology and retrospects some types of energy - saving systems for hydraulic elevators. then the working principles of the project are discussed and analyzed at four different working status, i. e. light load upwards, heavy load upwards, light load downwards and heavy load downwards. and the chapter focus on the introduction of structure design of pump station, calculation and type selection of pump / motor reversible units, research on oil leakage principles of accumulator circuit, design of accumulator - pump / motor pressure - energy transformer and integrated valve blocks, etc. the last but not the least, the electrical wiring of vector inverter control cabin and design of computer control and data acquisition system are introduced

    論文第二章首先簡單介紹了交流異步電動機變頻調速技術的發展概況，在回顧電梯液壓控制系統節能技術的基礎上，介紹了本課題研製的「採用蓄能器的液壓電梯變頻節能控制系統研究」的基本原理，分析了動力系統在電梯轎廂輕載上下行、重載上下行等四種典型工況下的基本工作狀態和工作方式；詳細地介紹了本課題節能系統液壓動力泵站的結構設計和參數設計，重點研究了液壓動力泵站的結構設計、液壓泵馬達可逆性問題及其選型設計計算、蓄能器迴路泄漏油損失機理的研究及其補償裝置的設計、蓄能器-泵馬達壓力能量轉換裝置的設計、多功能集成控制閥組的設計等內容；最後簡單介紹了本課題矢量控制變頻控制櫃的外部附件電氣接線、計算機控制及數據採集系統的硬體設計等內容。
  13. Using artificial neural network, a new approach to process flight dynamic datum is presented, and a fault aircraft flight simulation system is established

    並提出了一種利用神經網路來處理氣動力模型數據的方法，建立了故障飛機模擬系統。
  14. Moreover, in order to capture the linear properties in aerodynamic coefficients, additional linear terms are added to the model, which make the wavelet network model has some definite physical significance in use

    另外，本文在小波網路模型中加入狀態變量的線性項，以反映氣動力系數中的線性特性，這對于實際應用是非常有意義的。
  15. Then, after introducing wavelet analysis and wavelet network basic theory the thesis begin to study the modeling criteria with optimizing algorithm, and design the structure of wavelet network

    其次，在介紹完小波分析及小波網路的基本理論知識后，針對氣動力系數建模，對小波網路的建模準則及優選演算法進行了研究，並完成網路結構的設計。
  16. Aerodynamic coefficient identification is a interdisciplinary subject between mechanics, informatics and control theory. this thesis also gives an overview of the development direction in this field, especially introducing the application of neural network in the aerodynamic coefficients identification, which gives the theoretical basis of using wavelet network in modeling of aerodynamic coefficients

    氣動系數辨識為介於力學、信息學和控制論之間的一門交叉學科，本文對該領域的發展方向進行了分析，其中特別分析了神經網路在氣動力系數建模中的應用狀況，這為本文採用小波網路氣動系數建模打下理論基礎。
  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. Based on in - depth survey of mess references, this thesis firstly gives comprehensive overview of aerodynamic coefficient modeling and corresponding parameter estimation algorithm

    首先，本文在查閱大量近年國內外相關文獻的基礎上，對飛行器氣動力系數建模理論及相應參數估計演算法進行了綜述。
  19. In the result with lateral jets, the structure of jets, the pressure of projectile surface and the aerodynamics characteristics are all in steady periodical fluctuation

    彈丸側噴流場干擾波系的空間結構、彈體表面壓力和各種空氣動力參數均表現為穩定的周期性波動。
  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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