aerodynamic configuration 中文意思是什麼
aerodynamic configuration
解釋
空氣動力布局- aerodynamic : adj. 空氣動力學的。 an aerodynamic missile 飛航式導彈，有翼導彈。n. -s 空氣動力學，氣體力學。
- configuration : n. 1. 結構；構造；圓形，外形。2. 組合，布置；配置。3. 地形；【天文學】（行星等的）相對位置，方位；【化學】（分子中原子的）組態，排列；【物理學】位形；組態。
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Tailless flying wing aerodynamic configuration being optimal selection in ucav general layout design
大展弦比復合材料機翼結構建模與氣動彈性分析 -
Force measurement in a low speed wind tunnel was conducted to investigate the effects of the height of a distant canard wing on the longitudinal aerodynamic characteristics of a forward - swept configuration
摘要基於前掠翼鴨式前翼布局的風洞測力實驗，分析了距離主機翼較遠的鴨翼相對于主機翼的高度對布局縱向氣動性能的影響。 -
This paper has mainly made a research on the aerodynamic configuration design of " w " tailless aircraft and the design idea has been presented here. according to the configuration design requirement of certain uav, aerodynamic configuration design has been carried out and two configuration projects are given out at last : forward - swept wing tailless configuration and " w " tailless configuration. the longitudinal and lateral aerodynamic characteristics are obtained by using two aided soft : ug to build up geometrical models and mgaero to calculate flow field
本文研究了「 w 」型無尾布局的氣動外形設計，闡述了該布局的氣動設計思想，根據型無人機的總體設計技術指標，進行了氣動外形設計，提出了兩種氣動布局方案：前掠翼無尾氣動布局和「 w 」型無尾氣動布局，利用ug建模軟體和mgaero氣動分析計算軟體計算了兩種布局的縱、橫向氣動性能，分析了前掠翼前緣掠角和翼身融合對氣動性能的影響，計算結果表明， 「 w 」型氣動布局的設計思想是正確的，所設計的「 w 」型無尾氣動布局方案的氣動性能優越，超過了總體設計技術指標。 -
The investigation on " w " aerodynamic configuration has acquired primary achievements, but there is still many work need to do. the further study is the folio wings : 1
有關「 w 」型無尾氣動布局的研究取得了初步的成果，但還有許多工作要做，需要進一步開展的工作主要有： 1 -
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 -
Therefore, in this paper the multi - objective optimization design of aerodynamic and stealthy configuration for the fighter is discussed according to the geometrical characteristics of the advanced tactical fighter. the work is performed as follows : 1 according to the different design requirement in subsonic and supersonic state, with the multi - objective optimization method, the aerodynamic configuration optimization method for different design requirements has been obtained
基於以上考慮，本文從研究氣動隱身多目標優化問題的角度出發，針對先進戰斗機的外形設計特點，完成了以下工作： 1 、針對現代戰斗機亞、超音速的不同設計要求，利用多目標優化設計方法建立了可進行滿足不同設計要求的氣動外形優化設計方法。 -
2 to meet the need of aerodynamic configuration optimization design in supersonic state, different supersonic drag prediction methods have been compared and the supersonic performance calculation method suitable for optimization design system has been obtained
為適應超音速氣動外形優化設計要求，對不同的超音速阻力計算方法進行了比較計算和分析，建立了與優化設計相適應的超音速氣動特性計算方法。 -
During the procedure, the airspeed continues accelerating ( or decreasing ) and the aircraft configuration is rapidly changing. the aerodynamic interactions are complex and lead to dynamic instabilities. the shift between helicopter and airplane flight modes necessitates a change in control strategy
過渡模式下，飛機速度不斷增加（或減小） ，氣動布局不斷改變，飛機動力穩定性差且氣動干擾嚴重，直升機控制和固定翼控制切換，因此過渡模式動力學特性和控制系統研究是整個傾轉旋翼飛機研製的主要難點。 -
Experimental investigation of aerodynamic configuration for mavs
微型飛行器相關布局氣動特性實驗研究 -
Particularly, the parameterized design technology of three - dimensional configuration, the woodward panel method calculating aerodynamic performance, the pixel method calculating the rcs of target ' s surface, the shooting and bouncing race ( sbr ) method calculating the rcs of cavity, and the phase coupling method calculating the rcs of whole missile are researched in this paper
主要應用研究了用於巡航導彈的參數化三維幾何造型技術、計算氣動性能的伍德沃德面元法、計算目標體表面rcs的象素法、計算腔體rcs的射線跟蹤法與計算整體rcs的相對相位疊加法。 -
In this paper, an integrated calculate method including three - dimensional configuration design, aerodynamic analysis, and computation of radar cross section ( rcs ) is researched
本文對與導彈總體設計密切相關的三維幾何造型、氣動性能與雷達散射特性的一體化計算作了相關研究。 -
On the base of the soft about the deformation of aerodynamic configuration of mav, the advanced controlling technique of the deformation o f aerodynamic configuration about the prototype mav will be explored. based on the characteristic of micro air vehicle, this paper abstracted the aerodynamic evaluation mathematics models, developed a aerodynamic engineering estimation program, all kinds of aerodynamic configuration was compared and analyzed, found the perfect configuration and got the prototype of mav. abstracted the model about the deformation of aerodynamic configuration on base of the method of vortex lattice, developed the program for researching the performance of the deformation of aerodynamic configuration
本文針對mav的具體特點，抽象出mav的氣動工程計算數學模型，建立起氣動工程估算環境，對各種氣動布局進行了氣動特性比較分析與綜合，尋求出理想的mav氣動布局方案並提出mav原型機，抽象出基於渦格法的氣動外形形變的數學模型，建立起氣動外形形變性能研究環境，探討新型的飛行控制方法和氣動力控制策略，在得出氣動外形形變模型的初始方案后，對其進行進一步的優化，最後得出理想的氣動外形形變執行機構組合陣列。 -
Instead, the controlling according to attitude - controlling of the deformation of aerodynamic configuration is new and advance measure, which has great probability to supply the gap in researching of the control technique of mav. this paper aims that three varied configurations of micro air vehicle will be designed and optimized, then their aerodynamic property will be compared and analyzed, and the prototype of mav will be got
本文旨在對各種氣動布局的mav進行氣動特性比較分析與綜合，得出最適合於mav的原型機，在建立一套基於氣動外形形變的性能研究環境的基礎上，對該原型機進行氣動外形形變先進控制策略的探索。 -
The research in this paper is granted by the item of national natural science foundation of china, the research of mav control base deformation of aerodynamic configuration ( no : 60175032 ), it is the ground work of developing innovative control scheme
本文的研究工作是在國家自然科學基金項目? ?基於氣動外形變形的mav控制問題研究（編號為60175032 ）的資助下開展的，是進行mav新穎控制方案研究的基礎性工作。 -
In chapter 6, a new idea for simulating rotor bvi noise experiment is presented using a scissors rotor configuration with the vertical separation between a pair of rotors, based upon the fact that the important aerodynamic feature of this scissors rotor configuration is its close blade - vortex encounter. and the models and facilities designed for the bvi noise experiment are given
在第六章，基於槳-渦靠近通過是非共面剪刀式布置旋翼流場的一個重要特徵，提出了使用剪刀式布置旋翼來模擬旋翼槳-渦干擾噪聲實驗的新構想，並設計了用於噪聲實驗的模型。 -
The design idea of " w " tailless aerodynamic configuration has been presented which has independent knowledge property right
提出了具有自主知識產權的「 w 」型無尾氣動布局的設計思想。 -
Also longitudinal aerodynamic characteristics of missile are investigated. the traditional dependence on wind tunnel experiment is changed greatly : firstly, the aerodynamic characteristics of missiles with complex configuration are solved satisfactorily, especially integral rocket - ramjet missile ; secondly, feasibility of n - s equation to numerical simulation of inner and outer fiowfield of missile with complex configuration is discussed
（ 3 ）採用n - s方程方法數值模擬某型整體式沖壓發動機導彈的全彈內外流場，研究了導彈的縱向氣動特性，改變了過去依賴于地面風洞試驗結果的傳統做法。
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