尾翼翼型 的英文怎麼說

中文拼音 [wěixíng]
尾翼翼型 英文
tail profile
  • : 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...
  • 尾翼 : [航空] tail surface; empennage; tail; tail assembly; tail fin; tailpiece
  1. Double - wing micro air vehicles adopts the aerodynamic shape : no tail, only wings and vertical tail placing in wing

    式微飛行器採用無式,且只有機,垂也置於機上的氣動布局。
  2. The wake survey cannot be used to measure the drag of stalled airfoil or of airfoils with flaps down.

    流測量不能用來測量失連狀態下的冀或襟偏轉后的阻力。
  3. Finite element analysis of empennage of a special bullet

    特種彈片的有限元分析
  4. Chang zhou ming yang the car accessories limited company is a profession to produce every kind of car type top tail clear water pot, wash away dirt pot well ventilated tube, brake oil cup etc. heavy type the fuel on the car a freshet a tool box. every kind of hollowness blow the a business enterprise for producting, and every kind of combination tool box etc. product, the product category is numerous, the equipments is well - found, through the experience backlog of few decadeses, the product quantity promotes continuously, the production scale extends gradually, can produce the specification minimum 50 grams of, biggest 15000 grams of, length is 1. 6 hollowness of rices blows a pack. product regardless in molding tool design, or production line, all already beyond the reach of the domestic goes together. my factory can also according to customer the need of the product specification, color and luster, come to kind design to order the system

    常州市明煬汽車配件有限公司是專業生產各種車清水壺,洗滌壺通風管剎車油杯等。重汽車上的燃油箱澎漲水箱塑料工具箱。各種中空吹塑箱包製品及各種組合工具箱等產品的企業,產品種類繁多,設備全,經過數十年的經驗積累,產品質量不斷提升,生產規模逐步擴大,能生產規格最小50克,最大15000克,長度為1 . 6米的中空吹塑產品。
  5. 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、不同位置分叉點及緣剖分角對魚形舵影響下的升力。
  6. 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

    為了使數學模更貼近生物模,本文又將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,柔性使得平均推力減小,但是,對具有相同推力的柔性比剛性具有更高的效率。
  7. The november 12 crash of flight 587 in new york city, in which the tail fin, or vertical stabilizer, of an airbus a300 fell off, raised concerns about the increasing use of composites over metal

    去年11月12日在紐約市墜毀的587號班機,是由於該架a300空中巴士的,或稱垂直平衡器,從機身脫落所致;因此有關復合材料日益取代金屬的使用情況,引起大眾關切。
  8. In chapter 2, a simplified analytical model is presented for the analysis of the bvi mechanism, adopting the beddoes " prescribed wake model. by this model, the azimuthal location and miss - distance of the bvi and the radiation directivity of the bvi noise are calculated and discussed, and some conclusions are obtained

    在第二章,使用beddoes預定跡模,建立了一個用於旋槳-渦干擾特性機理分析的簡化數學模,分別對旋槳-渦干擾位置、槳-渦干擾距離和聲輻射方向性等進行了計算和分析,得出了有意義的結果。
  9. In chapter 5, a new dynamic wake model is developed by employing the rotor free - wake method in chapter 2, and is used to investigate the curve distortion during the conversion of tiltrotor aircraft between helicopter flight conditions and airplane flight conditions

    在第二章方法的基礎上,第五章建立一個傾轉旋動態跡模,使用該模對傾轉旋機傾轉過渡狀態的跡彎曲變形進行了研究,得出了一些結論。
  10. Enhanced unsteady and nonlinear rotor wake model for real - time flight simulation

    一種適合飛行模擬應用的非定常非線性旋跡增強模
  11. < uk > the configuration has two tractor propellers, full - span double slotted flaps deflected 45, and a high tail. < / uk >

    < uk >實驗模有二兩拉力螺旋槳,全展雙縫襟偏轉45 ,並有高置的水平。 < / uk >
  12. The configuration has two tractor propellers, full-span double slotted flaps deflected 45°, and a high tail.

    實驗模有二兩拉力螺旋槳,全展雙縫襟偏轉45,並有高置的水平
  13. Additionally, small winglets / stabilizers with no other discernable purpose are okay to be used as greeble ( pointless, extraneous detail ) as long as they aren ' t a major portion of the model, and if the model wasn ' t designed for pure space usage in mind

    另外,如果模不是只純粹用於太空,小/水平上有些突起(沒有實際意義的細節)只要不讓人覺得是模的主要部分,這都是允許使用的。
  14. The main work in this paper includes three parts : the theory research on partially - cavitating and super - cavitating axisymmetric bodies, the numerical computations and experimental investigations on partially - cavitation and super - cavitation on axisymmetric bodies. after finishing the study of theory and experiment on the partially - cavitation and super - cavitation for axisymmetric body, i use the potential flow theory to build the mathematical model on the partially - cavitation and super - cavitation for axisymmetric body. many cavity wake models, such as pressure recovery close model, riabouchinsky model and re - entrant jet model, are studied seriously

    本文在深入研究了回轉體局部空化與超空化理論及實驗結果的基礎上,基於勢流理論,建立了回轉體局部空泡和超空泡流場的基本數學模,通過對kinnas和fine 、 uhlman以及jiedang和gertkuiper等人基於二維水提出的壓力恢復閉合模、鏡像板模和回射流模等空泡流模進行了逐一的研究分析,發現其中的壓力恢復閉合模較適用於模擬回轉體空泡部流場,並選用此空泡流模作為求解回轉體空化流場正問題與逆問題的數學模的組成部分。
  15. Study on the impact of x - tail on static stability for an uav

    布局對無人機靜穩定性的影響
  16. Lastly, previous vane are analysed by fluent, we calculate the pressure distribution chart and report chart of each wing form, then alter the torsion angle and the airfoil form of the vane respectively, finally ascertain the influence curve of the torsion angle and the airfoil form of the vane on which act the lift power

    最後,通過fluent對設計出的葉片分析,得出其壓力分布圖和報告圖。然後從改變葉片的扭轉角度和兩個方面分析其對升力和阻力的影響。得出葉片的扭轉角和對升阻比的影響曲線,在文章的結部分估算了無人機的一些性能參數。
  17. This thesis is a fem analysis of opening process of the folded horizontal tail wing of some aircraft, and the work includes modeling the detailed mechanic assembly of the tail wing, and computing its elastic dynamic process by large - scale fem software system, ansys and ls - dyna3d, as well with the postprocessor tool - lspost to take the computational results into visualization

    本文運用大有限元cae軟體ansys和ls - dyna3d對某具體飛行器水平折疊的機構運動進行了細致的有限元建模和動力學計算分析,運用lspost對計算結果進行了詳細的后處理,運用可視化技術對數值分析結果進行了圖形及曲線描述。
  18. The material characteristic and principle of piezoelectric material ( pzt ) and macro - fiber composite ( mfc ) is analyzed. cada - x structural dynamics analytic software is used to carry on the experimental modeling and mode analysis of the vertical tail. consequently, the disposal scheme of sensor and actuator is confirmed

    本文的主要研究內容為:一、分析了壓電陶瓷和壓電纖維復合材料的特性及工作原理,採用比利時lms公司的cada - x結構動力學分析軟體對進行實驗建模與模態分析,根據模態實驗結果,確定了傳感/驅動元件的布置方案。
  19. Abstract : on the basis of setting up the angle motion mathematic model of the terminal correct projectile forced by impulse corrective force, this paper discusses the dynamic response of the terminal correct projectile and response spectrum. the general conclusion that profit to design impulse correct projectile stabilized by taifl wing is given

    文摘:建立了末段脈沖修正彈在脈沖修正力作用下的角運動數學模,分析了末段修正彈對脈沖修正力的動態響應特性和響應譜,給出了對穩定脈沖修正彈設計有普遍指導意義的結果。
  20. This paper aims at model of vertical tail based on certain type aircraft. the method of distributed actively vibration control based on multi dsp has been carried on this model. a distributed actively vibration control system based on dsps is designed to real timely control the structural vibration of two modes

    本文以某飛機的為目標,採用基於多dsp處理器的分散式控制方法實現對垂直的振動主動控制,開發出了一套基於dsp的振動主動控制系統,針對結構的兩階模態振動實施了分散式振動主動控制,並進行了相關的理論和實驗研究。
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