氣動力方法 的英文怎麼說

中文拼音 [qìdònglìfāngfǎ]
氣動力方法 英文
aerodynamic tool
  • 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...
  • 方 : Ⅰ名詞1 （方形; 方體） square 2 [數學] （乘方） involution; power 3 （方向） direction 4 （方面） ...
  • 法 : Ⅰ名詞1 （由國家制定或認可的行為規則的總稱） law 2 （方法; 方式） way; method; mode; means 3 （標...
  • 方法 : method; means; way; technique; process; procedure; plan; device; recipe; fashion; tool; maneuver
  1. By means of guidance command decomposed forwardly, the combined control system is divided into two parallel subsystems : the aerodynamics subsystem and the direct force subsystem

    復合控制採用對制導指令進行前向分解的方法，將復合控制系統分為兩個并行的子系統，即氣動力控制子系統和直接力控制子系統。
  2. 4. the combined control system was designed. by means of control command decomposed forwardly, the combined control system was divided into tow parallel subsystems, namely the aerodynamics subsystem and the direct force subsystem

    復合控制系統採用對控制指令進行前向分解的方法，將復合控制系統分為兩個并行的子系統，即氣動力控制子系統和姿控直接力控制子系統。
  3. Method study of normal force engineering calculation of missile with rectangular cross - sectional shape

    矩形截面彈體法向氣動力計算方法
  4. The paper analyzes the characteristic of aerodynamics with structure of helicopter propeller blade, dissertrates vortex theory and the theory about gliding air field which produce the power of helicopter propeller blade. at the same time it also deduce the method of computing the induced velocity produced by helicopter propeller blade with vortex theory. at last, an influcence to the spreading of sound is discussed

    並且將兩種定位演算法進行了比較，說明了優劣；結合直升機的結構分析了旋翼的空氣動力特性，論述了直升機旋翼產生拉力的滑流理論和渦流理論，結合渦流理論論述了直升機旋翼流場誘導速度的計算方法，在此基礎上分析了直升機旋翼流場對聲音傳播的影響。
  5. Laboratory methods of testing air curtain units for aerodynamic performance rating

    空氣動力學性能指標用風簾裝置測試的實驗室方法
  6. The ejected coolant interacts with the external flow near the endwall and generates aerodynamic and thermodynamic losses in the process. this reduces turbine stage efficiency and together with the consumption of cooling air is detrimental to the overall cycle efficiency

    但這種方法中噴射的冷空氣與端壁附近的外流場相互作用產生氣動力和熱動力損失，並且消耗冷卻空氣，從而損害渦輪的整體循環效率。
  7. According to the measuremental data of the two ammunications, the anti - designed computation and analysis of aerodynamic characteristic, flight stability, exterior ballistic characteristic for the two ammunications are studied with the advanced methods of the exterior ballistics. using the monte calo algorithm, the statistic mathematical model about ammunication ' s intensity is established and the 1000 miter vertical target intensity and the fall intensity are discussed in detail for the two ammunications. the improval potential and the main technical approachs of these ammunication ' s exterior ballistic performances are presented by compositive optimal algorithm

    根據工廠對俄ak130艦炮彈藥的測繪數據，利用先進的外彈道數值分析方法對兩種彈藥的空氣動力特性、飛行穩定性特性、外彈道特徵量等進行了反設計計算分析；採用montecarlo方法，建立了艦炮彈藥密集度性能統計分析數學模型，對兩種彈藥的立靶密集度和地面密集度進行了詳細的計算分析；利用外彈道性能綜合優化設計方法對兩種彈藥的外彈道性能指標的改進潛力和主要技術途徑進行了分析。
  8. 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。
  9. Fuzzy logic technique of unsteady aerodynamic ident ification

    非定常氣動力辨識的模糊邏輯方法
  10. Methods for testing and rating induction units for air distribution systems - thermal and aerodynamic performance

    空氣分配系統用感應裝置試驗及評定方法.第1部分:熱特性和空氣動力特性
  11. ( 2 ) transient jet - interaction phenomena, challenge project, is analyzed by computational unsteady aerodynamic method. boundary condition of transient jet is established

    （ 2 ）將非定常空氣動力學數值計算方法創造性地應用於姿態控制發動機瞬態流場計算。
  12. 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。
  13. In the thesis, most advanced, relative, foreign high - tech has been pursued. feasibility analysis has n ' t been carried out by synthesizing much relative knowledge such as electromagnetism theory, plasma technology, aerodynamics, electronic technology etc until the scheme is confirmed, that is, a uniform, one atmosphere, controllable, glow - charge surface plasma can be generated and flow can be accelerated by changing electric field

    本文追蹤目前國外最先進的技術，綜合電磁理論、等離子體技術、空氣動力學、電子技術等相關知識進行可行性分析，確定了研究方案，即利用電流體力學（ ehd ）方法在一個大氣壓下產生高效、均勻、可控的射頻輝光等離子體，同時，通過改變電場促使流動加速。
  14. The aerodynamic parameters are calculated under dynamic condition. according to the position and the posture of the bomb, the parameters are calculated every short interval until it leaves the interfere area

    本文採用了在動態條件下求解航彈氣動力的方法，每隔很短的一個時間間隔就根據彈體的位置和姿態重新計算其氣動力參數，直至航彈脫離機翼、機身的干擾區。
  15. Compared with a delta wing aircraft, the double - delta wing configuration has better aerodynamic performance at high angles of attack. an operational analysis was introduced as a method for evaluating training effectiveness of trainer aircraft. approaches to the engineering estimation of aerodynamic characteristics for aircraft with a double - delta wing configuration were studied, and the procedures for determining aircraft performance indices formulated. taking training effectiveness as the objective function and geometric parameters of the wing platform as design variables, through a numerical multivariate optimization arithmetic, the conceptual design optimization for a certain fighter trainer aircraft with double - delta wing configuration was carried out under the constraints of tactical and technical requirements and interrelated geometry. agreement of a calculation example with engineering practice indicates that the optimal design has higher training effectiveness than the baseline design, and in addition, improves the structural force - bearing conditions

    雙三角翼氣動布局比三角翼飛機具有更好的大攻角空氣動力特性.引入了評估教練機訓練效能的作戰分析法，研究了雙三角機翼布局飛機空氣動力特性的工程計算途徑以及飛機性能指標的確定方法.以訓練效能作為目標函數並選取機翼平面形狀的幾何參數為設計變量，採用多變量數值尋優方法，在戰術技術指標及相關幾何約束條件下，對某高級教練機的雙三角機翼氣動布局方案進行了優化選擇.算例表明最優方案不僅比原準方案具有更高的訓練效能，還改善了結構的受力情況，與工程實踐吻合
  16. Using above methods to solve unsteady pressure distribution, coupling structure equations, the supersonic or hypersonic aeroelasticity is simulated in time - domain

    運用上述的非定常氣動力求解方法，耦合結構動力學方程，實現超音速、高超音速氣動彈性的模擬。
  17. Analyzing existing engineering methods, we combine them in such a way to make computing aerodynamic characteristics possible for arbitrarily shaped body

    驗證、分析了各種超音速、高超音速氣動力工程計算方法，將各種工程方法統一起來，用於求解任意外形的飛行器氣動力。
  18. Employing euler based steady solution and piston theory, a new method ( we call it local piston theory in this paper ) to solve supersonic or hypersonic unsteady loads has been developed

    發展了一種運用定常cfd方法和活塞理論求解超音速、高超音速非定常氣動力的新方法?當地流活塞理論。
  19. 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。
  20. 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
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