翼面 的英文怎麼說
中文拼音 [yìmiàn]
翼面
英文
aerofoil-
The new technique allows first order shear deformation plate theory ( fsdpt ) or classical plate theory ( cpt ) to be used for modeling built - up wing structures, sandwich wing structures or the wing structures which the volume between upper and lower skin is empty or solid with a ' general planform
根據翼面的幾何和結構特點，新技術能夠自主選擇經典板理論（ classicalplatetheory ，簡稱cpt ）或第一階剪切變形板理論（ firstordersheardeformationplatetheory ，簡稱fsdpt ） ，具有模擬空心、實心、夾層和組合等形式的翼面結構及三維建模的能力。Investigation on application of gurney flap to triplane configuration aircraft lift - enhancement
襟翼增升技術在三翼面布局飛機模型上應用的實驗研究First, the repeated structural analyses for static and dynamic characteristics are needed in the integrated optimization of composite wing structures. in this situation, the finite element model ( fem ) is time - consuming, while the continuum equivalent plate model ( epm ) is more efficient and often used
首先，復合材料翼面結構綜合優化設計需要反復進行結構靜力和動力特性分析，如果採用有限元模型（ finiteelementmodel ，簡稱fem ） ，則其工作量太大。These hinged flight surfaces could deflect airflow to modify the lift, thereby supplying roll control
這些以鉸鏈連接的飛行翼面能夠偏轉氣流以調整升力，進而控制滾轉。Creative design of folding fin mechanisms of missile based on yan ' s mechanical creative design procedure
基於顏氏機構創造法的導彈翼面折疊機構方案創新設計A part or surface, such as a wing, propeller blade, or rudder, whose shape and orientation control stability, direction, lift, thrust, or propulsion
翼剖面；機翼；翼面一個部件或平面，如機翼、螺旋槳葉、方向舵等，其形狀或方位控制穩定性、方向、抬升、沖擊或驅動Application of topology optimization technique to the conceptual design of aircraft movable surfaces
自動化技術在飛機活動翼面結構方案論證中的應用Mongolian gull : pale upperside, clear contrast between black primaries and pale blue - grey upperwing, strikingly white head, typically two quite large mirrors on p10 and p9
蒙古銀鷗:淡色的上翼面，黑色初級飛羽和淡藍灰色上翼面間明顯的對比，顯著的白色頭部，典型地在p10及p9上有二個相當大的翼鏡Vega gull : pale upperside, clear contrast between black primaries and pale grey upperwing, dirty head ( may be almost hooded, with very heavy, wide, blob - shaped brownish marks ), more rounded wing, some have bright raspberry - pink legs
織女銀鷗:淡色上翼面，黑色初級飛羽和淡灰上翼面間明顯的對比，污色的頭部（可能幾乎罩住頭頂，非常深，寬，點狀的棕色斑點） ，比較圓弧的翅膀，有些有明亮的覆盆子般粉紅的腳A second method is to furnish the surfaces with hinges and to use an exterior sector with drilled holes for each angle setting.
第二種方法是在翼面上裝置鉸鏈，用一個對不同安裝角鉆有不同孔的外部扇形件與之配合。This one mongolian with white head, strong contrast between primaries and pale grey of upperwing and seven black - marked primaries
這只蒙古銀鷗有白色的頭部，初級飛羽和上翼面的淡灰色間的強烈對比，以及七枚帶黑色的初級飛羽Multi - gap - fowler - flap, while deflecting its rudders, simultaneously extends backwards by relatively large scope, which broaden the overall wing - camber and area, so that more additional lift could be attained through improving air - flow boundary layer
多縫富勒襟翼在襟翼舵面偏轉的同時發生較大幅度的後退，增加機翼整體彎度和機翼面積，通過縫隙氣流改善附面層狀況，因而得到加大的升力增量。In order to set up the dynamic model of swimming micro robot, this dissertation builds up the statics model and analyses the micro motion amplifying performance of micro robot mechanism, builds up the vibration model of micro robot and analyses the vibrating performance without and with damp, researches the propelling force of driven wing and the resistance of micro robot in liquid based on the theory of flat board resisting stream, builds up the dynamic model of swimming micro robot for the first time in nation and analyses its swimming performance which is influenced by driving signal frequency, amplifying performance of main machanism, area of driven wing, character of fluid and so on. this dissertation manufactures the micro robot and sets up the experimental environment and tests the amplifying effect and the vibrating performance
本文建立了主體機構靜力學模型，研究了主體機構的結構參數對微位移放大性能的影響；建立了主體機構振動模型，研究了主體機構在無液體阻尼和有液體阻尼情況下的振動特性；根據流體力學平板繞流理論，研究了驅動翼產生的推進力和微機器人在流體中受到的阻力；在此基礎上國內首次建立了泳動微機器人的動力學模型，並對模型進行了深入的研究，詳細闡明了驅動信號頻率、主體機構放大性能、主體機構振動特性、驅動翼面積、液體性質等因素對微機器人泳動特性的影響。Several non - linear phenomena are also analyzed. by using uncoupled thermal - structure analyzing method, with the consideration the additional stiffness caused by thermal stress, the finite element model for thermal - vibration analysis is obtained and two typical hypersonic wing structures are computed
運用非耦合熱-結構分析方法，考慮熱應力引起的附加剛度，得到熱環境下的結構分析的有限元模型，並計算了兩種典型結構的高超音速翼面熱結構。Moreover, in the application of aircraft structures design, the composite wing is still to meet the needs of aeroelastic design. through reading the aerodynamic influence coefficient matrix from the nastran file, this paper generates a static aeroelastic equilibrium equation and divergence eigen - equation, which is needed by the aeroelastic tailoring of composite wing. through this equation, the aeroelastic tailoring of composite wing and its optimization design have come into being
此外在飛機結構設計過程中，復合材料翼面結構還要滿足氣動彈性設計的需要，本文通過讀入由nastran所產生的氣動影響系數矩陣，構造出滿足復合材料氣動彈性分析所需要的靜氣動彈性平衡方程和發散特徵方程，並在此基礎上實現了復合材料氣動彈性剪裁優化設計。Study on aircraft wing structure about conceptual design method
飛機翼面結構概念設計方法研究A 4 - order runge - kutta method is used to solve the droplet trajectory equation in order to determine the droplet impingement zone. 4
採用經典的四階龍格-庫塔法對其求解，以確定水滴在翼面上的撞擊區。Numerical results are in good agreement with some data and the method and procedure presented in this paper are verified. and then the wing ? flutter characters of a missile wing are numerical simulated with the examples of a missile wing
以某導彈翼面為算例，對彈翼的亞、跨、超音速的顫振臨界速度進行了數值計算，部分計算結果與風洞計算結果相比較，一致性很好。Hdo divides the integrated optimization of composite wing structures into two sub - problems that are easy to be solved : upper level optimization and lower level optimization
它將復合材料翼面結構綜合優化設計問題分解成兩個易於求解的子問題：頂層優化設計和底層優化設計。Two important aspects of the integrated optimization of composite wing structures are focused in this thesis : design - oriented structural analysis methods and integrated optimization algorithms
因此，本文重點探討了復合材料翼面結構綜合優化設計問題涉及到的二個重要方面：面向設計的結構分析方法和綜合優化演算法。分享友人