旋翼槳葉 的英文怎麼說

中文拼音 [xuányìjiǎngyè]
旋翼槳葉 英文
main-rotor blade
  • 旋 : 旋Ⅰ動詞1 （旋轉） whirl 2 （用車床切削或用刀子轉著圈地削） turn sth on a lathe; lathe; pare Ⅱ名詞...
  • 翼 : Ⅰ名詞1 （翅膀） the wing of a bird 2 （像翅膀的東西） the wing of an aeroplane etc : 鼻翼 wing of...
  • 槳 : 名詞1. （劃船用具） oar; paddle 2. （螺旋槳） propeller
  • 旋翼 : helicopter rotor
  • 槳葉 : awe; paddle
  1. A board on a paddle wheel

    明輪翼螺旋槳上的寬闊葉板
  2. The two astazou turboprops are mounted in slender nacelles in the leading edges of the wings and drive three - blade propellers

    兩臺發動機安裝在機翼上小巧的發動機艙內，各驅動一個三葉螺旋槳。
  3. The smart rotor with active trailing edge is a new system for reducing the vibration which can adjust the air load of the blade to actively counteract the main harmonic of the force to the fuselage by controlling the deflection of the trailing edge

    主動后緣附翼控制是一種較新的旋翼減振系統，它通過控制后緣附翼的偏轉，調節槳葉的氣動載荷，實現對機體激振力主要諧波分量的主動抵消。
  4. 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
  5. Within this analytical model, the factors as unsteady aerodynamic and blade flap / lead - lag coupled motion are both considered

    旋翼機體耦合動力學模型考慮了非定常空氣動力和槳葉揮舞擺振運動耦合。
  6. Frequency tests of helicopter rotating rotor blade

    直升機旋翼旋轉狀態下槳葉固有頻率的測試
  7. The primary purpose of this paper is how to solve the overloaded propeller ' s condition. the style of propeller trailing edge cutting and shave on the pressure surface is adopted. the propeller ' s actual effect pitch will be reduced which cause the propeller ' s torque down

    本文主要是考慮螺旋槳出現負荷過重時如何處理的問題，所以採用槳葉隨邊切割並在葉面處將翼型修順的方式，實質上是切割后導致螺旋槳實效螺距的減小，從而使螺旋槳吸收的轉矩降低來達到主機負荷降低的目的。
  8. In addition, the dynamic equation of the rotor with trailing edges and the 2 - x actuator has been modeled for analyzing the aerodynamic performance of the rotor. the result of the analysis tells us that the performance of the rotor with trailing edges can get a remarkable improvement

    進而研究旋翼動力學模型，將推挽式雙x驅動器模型作為后緣附翼的一種驅動機構，分析旋翼的氣動性能，模擬運算結果表明，后緣附翼智能槳葉在各方面的性能都有顯著的提高。
  9. Main rotor blades were severed within the first few metres through contact with small trees and rocks, and the underbelly and right side of the fuselage were damaged substantially

    主旋翼槳葉在直升機沖前首數公尺處因碰觸地面矮小樹叢和石塊而斷裂，機腹和右側嚴重損毀。
  10. The left skid was substantially damaged. the main rotor blades remained intact but were bent and twisted

    主旋翼槳葉被折彎和扭曲，但保持完整。
  11. The design of structure and dynamics of a rotor blade is based on its section characteristic of composite blade

    因此，一個精確的剖面特性的分析計算方法對旋翼槳葉設計是十分重要的。
  12. Examination of the wreckage trail indicated that substantial damage was inflicted on the aircraft, in particular the main rotor blades, within the first few metres after initial impact

    墜機路線調查顯示，直升機尤其是主旋翼槳葉，在首次撞擊后的最初數公尺受損嚴重。
  13. To improve the stability, one common method is to install dampers at the roots of blades. however, commonly used dampers can hardly meet different demands when helicopter working in different conditions

    為提高旋翼/機體耦合動穩定性，一般採用在槳葉根部安裝減擺器的方法，但目前常用的減擺器很難滿足直升機不同工作狀態下對擺振器阻尼的不同需求。
  14. Damping was then determined via exciting the equation at the critical frequency to get the transit decay which was then analyzed with the moving - block method. in chapter 4, the nonlinear dynamic equation of rotor - body system with inter - blade dampers ( taking all possible attachment offsets into consideration, spanwise offset, vertical offset and in - plane offset ) was modeled

    本文重點推導了帶葉間減擺器（減擺器帶三個外伸量:展向，垂向和旋轉方向）的旋翼/機體耦合系統的非線性動力學方程，針對該方程提出了一種改進的多槳葉坐標變換方法。
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