展弦比 的英文怎麼說

Aeroelastic analysis of flexible large aspect ratio wing

特大展弦比機翼的特性與設計

Design and characteristics on wing of extreme big aspect ratio

大展弦比夾芯翼大攻角顫振分析

Three kinds of trapezoid, delta and airfoil shaped vortex generators are designed based on traditional, sub boundary layer and micro - vortex generators conceptual design, to study the influence of the shape, height, aspect ratio, chordwise position, spanwise position and direction angles of vortex generators on boundary layer separation control

（ 5 ）綜合分析研究了渦流發生器的工作原理和設計原則。根據國內外資料，研究了渦流發生器形狀、高度、展弦比、尖削比、弦向位置、展向位置和方位角等因素對附面層分離控制效果的影響。

The robotic fish model selected in this paper which consider an idealized bcf propulsive fish model that consists of only three links : the rigid body in the foreside ; the high aspect ratio caudal fin ; the caudal peduncle which connects the caudal fin and the body

機器魚的模型建立是把理想的bcf推進式魚類分為三個部分，分別是：前部剛性的身體，大展弦比的尾鰭和一個連接以上兩部分的尾頸。

The results of the lift interference are given here as a result of a series of rudder of different aspect ration fitted to different location of the fornication. in the second part, the device of open water experiment of ichthyoid rudder is present

提出了一個估算魚形舵定常升力的方法，計算了一系列不同展弦比、不同翼型、不同位置分叉點及尾緣剖分角對魚形舵影響下的升力。

In order to imitate tune tail fin better, a flexible fin only in chordwise is considered. results shows that flexibility can increase the propulsive efficiency and cause small decreases in the average thrust compared with a rigid caudal fin with similar motion. next, a comparison between the rectangle fin and the lunate fin is given

為了使數學模型更貼近生物模型，本文又將尾鰭處理為只考慮弦向變形而不考慮展向變形的柔性體，兩者對比的結果表明，柔性翼使得平均推力減小，但是，對具有相同推力的柔性翼比剛性翼具有更高的效率。

Flutter analysis of a high - aspect - ratio sandwich wing under large angle of attack

大展弦比飛機翼身結構不同剛度對結構響應的影響

Study on stability and manoeuvrability of flying wing aircraft

大展弦比機翼的氣動彈性問題探討

Design of innovative control surfaces of flying wing aircrafts with large ratio aspect

大展弦比飛翼布局飛機新型操縱面設計

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

Non - sinusoidal oscillation has the characters that the upward time of the continuous casting mold is longer than the downward time. it can reduce the friction between the mold wall and the strand surface, and prevents the strand from leaking and cracking, it can also improve the surface quality of slabs. it is the main development of continuous casting mold in the future

其中非正弦振動具有上升運動時間比下降運動時間長的特點，能減小結晶器與坯殼之間的摩擦力，防止坯殼的拉漏和拉裂，改善鋼坯的表面質量，是今後連鑄結晶器振動發展的主要方向。

The main work of this paper was as fellows : ( 1 ) generalized the development of pre - stressed steel structure in our nation and abroad, and pointed out the main problem in practice ; ( 2 ) presented the mechanism of pre - stressed steel structure and revealed its applicable range ; ( 3 ) established the optimization design model for pre - stressed steel structure, which accounts for constraints on stresses and displacements of structure ; ( 4 ) brought forward the optimization design method, which combined linear programming and the principle of full restriction, through which we can obtain the magnitude of each time pre - stress and the optimized sections of each members of structure ; ( 5 ) analyzed the best times of pre - stress and pointed out that 2 ~ 3 times is preferable ; ( 6 ) conducted optimization design on large - space steel roof, horizontal parallel steel truss with local cables, horizontal parallel steel truss with global cable, and ultra - static steel truss, the result of which indicated that the multiple pre - stress structure is very economic ; ( 7 ) compared different schemes of cable placement for horizontal parallel steel truss, and the results showed that the local cable only unloaded the second girders, but had no response on the first girders and stomach poles, while global cable could unload the second girders and the stomach poles outside of turning point of cable, thus proving that global cable is more economic than local - cable

本文的主要工作是：對國內外預應力鋼結構的發展歷史及現狀作了綜述和總結，指出當前預應力鋼結構工程實踐中存在的主要問題；闡述了預應力鋼結構的受力機理，並指出預應力鋼結構的適用范圍和特點；在考慮結構應力和變位約束的條件下，建立預應力鋼結構優化設計模型；提出多次預應力鋼結構優化設計方法和步驟，採用線性規劃和滿約束準則相結合的優化方法，可優化設計出施加的每一級預應力的大小，並得到結構各部分的優化截面；對多次預應力最佳的施加次數作了分析，並建議以2 3次為宜；為驗證文中理論和方法，分別對大跨多次預應力鋼屋架、局部布索的水平平行弦鋼桁架、整體布索的水平平行弦鋼桁架和局部布索的超靜定鋼桁架等算例進行了優化設計，經濟效益明顯；對水平平行弦鋼桁架的幾種施加預應力的方案進行比較，對于局部布索，預應力只對下弦起到卸載作用，對上弦和腹桿基本不起作用；而整體布索預應力除對下弦卸載外，對索折點以外部分腹桿也起到卸載作用，經濟效益好於局部布索。

Effects of different stiffness between wing and fuselage structures on structural responses for high aspect ratio airplanes

無人機大展弦比直機翼單雙機身布局對結構剛度的影響

The surface panel method has been applied to predict the hydrodynamic performance of highly skewed propeller. the surface of propeller and its trailing vortex are discreted by a number of small hyperboloidal quadrilateral panels with constant source and doublet distribution. for highly skewed propeller, the conventional method generating grid oriented along constant radii will result in a high aspect ratio and a high skewness and a twist panel near the propeller tip on blade surface, which result easily in incorrect calculation results of velovity on blade surface, even in iteration divergence and calculation failure. a “ non - conventional grid ” is developed to acoid these problems. this grid can effectively solve the problem of the calculation and convergence for highly skewed propeller. the non - linear kutta condition of equal pressure on upper and lower at the trailing edge is executed by the iterative procedure. by sample calculating, the obtained results are satisfied the experimental data

採用面元法預報大側斜螺旋槳水動力性能，螺旋槳表面及尾渦面離散為四邊形雙曲面元，每個面元上布置等強度源匯和偶極子分佈.對于大側斜螺旋槳而言，槳葉表面採用常規的等半徑網格劃分方法在近葉梢處將導致大展弦比、大側斜和扭曲面元，這容易使槳葉表面速度的計算結果不正確，甚至會導致迭代過程發散及計算失敗.文中建立了一種「非常規網格」劃分方法，能有效地解決大側斜螺旋槳的計算和收斂問題.槳葉隨邊處通過迭代實現非線性等壓庫塔條件

Optimal layout about wing amp; amp; fuselage on bi - fuselage aircraft with high aspect ratio straight wing

大展弦比聯接翼結構重量估算

For the first time, flight simulation related to high span - chord ratio uav based on variable windfield is executed, the facticity of windfield and its influence to flight performance curve are analyzed. 5

首次針對大展弦比無人機，進行變化風場中飛行模擬，討論各風場模型的真實性及其對飛行性能曲線的影響； 5

Discussion on aeroelasticity of large aspect - ratio wing

基於結構優化的大展弦比機翼質量估算

Structural stiffness effect of single amp; amp; bi - fuselage uav with higher aspect ratio and straight wing

大展弦比直機翼雙機身飛機中機身與機翼的最佳布置問題

In this dissertation, a hybrid optimization approach for automatic design of 3d turbine blades was proposed and well implemented. the applications to the stacking design optimization and full 3d aerodynamic design optimization for an annular cascade demonstrated the validity, robustness and efficiency of this hybrid approach

本論文提出和實現了一種適用於葉輪機械全三維氣動優化設計的方法，並利用該方法對某低展弦比、大折轉角的環形葉柵分別進行了基迭優化和全三維氣動優化。

Since it is the first use of the momentum - blade theory to predict cooling fan aerodynamic performance, the work presented in this paper is still open for further investigation

但由於本文使用的將動量?葉素理論運用到汽車冷卻風扇這種小展弦比的葉片的氣動計算上，尚屬首次，對于結果中存在的偏差的確切原因，尚有待于在今後的工作中繼續研究。