無翼型 的英文怎麼說

中文拼音 [wúyìxíng]
無翼型 英文
all-body configuration
  • 無 : 無Ⅰ動詞（沒有） not have; there is not; be without Ⅱ名詞1 （沒有） nothing; nil 2 （姓氏） a surn...
  • 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...
  1. Double - wing micro air vehicles adopts the aerodynamic shape : no tail, only wings and vertical tail placing in wing

    雙翼式微型飛行器採用無尾式，且只有機翼，垂尾也置於機翼上的氣動布局。
  2. 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。
  3. The equijpment is improved in design and is made into a fully automatic h - beam assembling machine referred to the same foreign sort of products. the positioning of the flange and web is performed through hte plus and minus screw mandrel drivenby the mtr accurately. and there is a highly precise coder to feedb - ack and show the accurate size on the unit set to guarantee the flanges, the webs with different width different width within the specified range for accurate positioning and automatic alignmet. there is no need to make adjustment each time

    該機是本廠參考國外同類產品基礎上改進設計而成的全自動h型鋼組立設備，其腹板翼板定位採用電機精確帶動正反絲桿夾緊，另一側設有小行程液壓夾緊，能確保規定范圍內的不同寬窄的腹板，翼板精確定位，自動對中準確，無須每次作調準。
  4. But the variation of its aerodynamic forces will induce flapping motion and produce the cyclic pitch on the main rotor blades by the bell mixing mechanism. in order to study the effect of bell - hiller stabilizer bar on helicopter stability and control, this paper first analyze the function and the principles, give the flapping equation and a flight dynamic model with bell - hiller stabilizer bar. and then works over the stability and control of uav r - 50 in hover and cruise condition, and analyzed the influence from parameters of the bar to it

    為了深入研究希勒伺服旋翼對直升機穩定性和操縱性的影響，本文首先分析了希勒伺服旋翼的功能和工作原理，推導了伺服旋翼的揮舞運動方程，建立了帶有希勒伺服旋翼直升機的飛行動力學模型，然後以yamahar - 50無人直升機為例，分析該直升機在懸停和前飛時的平衡、穩定性和操縱性，在此基礎上進一步研究希勒伺服旋翼設計參數變化對直升機穩定性和操縱性的影響。
  5. The design of configuration and other primary structures of the helicopter have been finished. in order to analysis the stability and control of the helicopter, a flight mechanical modeling has been founded based on a single - rotor helicopter

    本文以常規單旋翼帶尾槳的直升機配平和操穩計算方法為基礎，建立了帶涵道共軸式直升機飛行動力學模型，對碟形無人直升機進行了配平和操縱性和穩定性分析計算。
  6. So, when we get the dates of stress and distortion of wing ' s model structure, which have been calculated by computer, we can simulate the dates of the real wing ' s structure, which we will get through stress sensors and distortion sensors. when we transmit those dates to the center computer through remote wireless transmission devices, the computer will analyze those dates according as scientific fault criterion. so we can carry out the remote real - time health monitoring for wing ' s structure

    這樣，我們讀取計算出的機翼結構模型在受力時的應力、變形值就可以模擬出在採用實體機翼作為研究對象時應力、變形傳感器傳回的數據，把這些數據通過遠程無線數據傳輸設備傳到數據處理計算機上採用科學的故障判據對這些數據進行處理就可以實現對機翼結構的實時遠程健康監控。
  7. 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。
  8. Only clouds of points instead of grids are distributed over the computational domain and the spatial derivatives are estimated using a least - square curve fit on local clouds of points. the paper gives discrete form for euler equations on base of gridless method, and adopts five steps runge - kutta scheme for time - marching. the numerical results have been obtained for the 2 - d flows over airfoils or multi - element airfoils using the method presented

    本文首先對無粘euler方程進行無網格離散，並運用顯式runge - kutta格式推進求解，成功地數值模擬了二維單段和多段翼型的繞流；在此成功的基礎上通過在euler方程的右端加入粘性項，使求解方程變為層流navier ? stokes方程，得到了翼型繞流，數值結果顯示出粘性的影響。
  9. Study on the impact of x - tail on static stability for an uav

    型尾翼布局對無人機靜穩定性的影響
  10. 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翼型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翼型對升阻比的影響曲線，在文章的結尾部分估算了無人機的一些性能參數。
  11. Second, change the diaphragm ’ s space between, retain the other thing, analyze the influence of the stress and deformation of box ? girder cross section and the beam web. based on the analysis upwards, the writer studied the rule of the influence of the stress and deformation box ? girder cross section and the beam web with different diaphragm ’ s space between. according to the results of finite element analysis, the writer puts forward some suggestions which will provide some reference for the following design

    本文利用ansys有限元分析程序，對指定斷面，不同曲率的曲箱梁，建立完備的有限元模型，分別對二個方面的問題進行了分析:其一，通過對箱梁在有無跨中橫隔板時截面頂板及腹板的變形和應力分佈的對比分析，闡述了設置跨中橫隔板的重要性;其二，在相同工況下，通過改變橫隔板的設置間距，分析對箱梁翼緣及腹板的受力影響。
  12. A technology for designing a dishing axial - symmetric unmanned helicopter that based on a coaxial rotor system shrouded by a toroidal shell is studied in this thesis

    本文研究碟形軸對稱無人直升機的總體設計技術，這種特型的無人直升機是將一副共軸式旋翼置於涵道中，外形為碟狀。
  13. Analysis of rotor manipulation mechanism for unmanned micro helicopters

    微型無人直升機旋翼操縱機構設計及分析
  14. Though we may not be able to predict the future of the world, we can predict the future of the new zone of the hangzhou bay bridge : it will become a modernized and industrialized city south of shanghai, a green city on the hangzhou bay, a city with a large port and a logistic center, an industrial powerhouse on the hangzhou bay rim

    我們無法預知世界的未來，但可以預知杭州灣大橋新區的未來，它將成為上海南翼的工業化現代城市，杭州灣畔的綠色濱海城市，東方大港的物流型港口城市和環杭州灣產業帶的金色港灣。
  15. As the driver of the micro multi - rotor craft, the micro bldc motor was of simple structure, easy fabrication, non commutation spark and so on

    摘要作為多旋翼微直升機的驅動器，微型無刷直流電動機具有結構簡單、製造方便、無換向火花等特點。
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