旋翼特性 的英文怎麼說

中文拼音 [xuányìtèxìng]
旋翼特性 英文
rotor characteristic
  • 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...
  • 特 : Ⅰ形容詞（特殊; 超出一般） particular; special; exceptional; unusual Ⅱ副詞1 （特別） especially; v...
  • 性 : Ⅰ名詞1 （性格） nature; character; disposition 2 （性能; 性質） property; quality 3 （性別） sex ...
  • 旋翼 : helicopter rotor
  • 特性 : characteristic（s）; character; performance; features; properties; behaviour; response; character...
  1. A mathematical model reflecting the tilt rotor unsteady and nonlinear aerodynamic characteristics in the longitudinal channel is presented in the paper. in the full flight envelope, the rotor thrust continues tilting and the aerodynamic forces of each component change as a function of airspeed and nacelle angle

    在整個飛行包線內，旋翼的推力矢量方向不斷變化，飛機各部件的氣動力隨發動機短艙傾角和空速的變化而變化，因而飛機的飛行動力學有很強的非定常、非線性特性。
  2. Variable diameter rotor is an effective method to improve the aerodynamic performance of tilt - rotor in both hover and cruise state. on the basis the research before, the variable diameter tilt rotor structure design has been finish, and in virtue of the technology of virtual prototyping to simulate and analyze the kinetic, dynamic and intensity property of it

    變直徑傾轉旋翼能有效的改善傾轉旋翼機懸停和巡航狀態下的氣動效率，本文提出了變直徑傾轉旋翼試驗模型設計方案，完成了可變直徑傾轉旋翼的結構設計，並利用虛擬樣機技術對變直徑傾轉旋翼的運動特性、結構動力學特性以及結構強度進行了分析、研究。
  3. The paper analyzes the characteristic of aerodynamics with structure of helicopter propeller blade, dissertrates vortex theory and the theory about gliding air field which produce the power of helicopter propeller blade. at the same time it also deduce the method of computing the induced velocity produced by helicopter propeller blade with vortex theory. at last, an influcence to the spreading of sound is discussed

    並且將兩種定位演算法進行了比較，說明了優劣；結合直升機的結構分析了旋翼的空氣動力特性，論述了直升機旋翼產生拉力的滑流理論和渦流理論，結合渦流理論論述了直升機旋翼流場誘導速度的計算方法，在此基礎上分析了直升機旋翼流場對聲音傳播的影響。
  4. 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預定尾跡模型，建立了一個用於旋翼槳-渦干擾特性機理分析的簡化數學模型，分別對旋翼槳-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。
  5. Pitch control system consist of three channels which is formed by three drive units. base on need of bench, drive system scheme is designed. single channel three - loop position servo system which is formed by linear motor is simulated. then kinetic behavior of rotor and system ’ s force coupling relation is analyzed. a compensation method for dynamic load which is caused by rotor rotation is presented base on structure - invarient theory

    根據實驗臺的技術要求，設計了整個驅動系統方案。對由直線電機構成的單通道三環位置伺服系統進行了設計和模擬。分析了旋翼運動的動力學特性、系統力耦合關系，並根據結構不變性原理對由旋翼運動產生的動態載荷提出了補償方法。
  6. Because of the periodicity of the hub oscillatory load and the nonlinearity of the i / o relationship of the smart rotor, the neural control methods with both off - line and on - line modeling in frequency domain on the smart rotor and their realization procedures are presented

    飛行中直升機的槳轂交變載荷以周期性的為主，而智能旋翼的輸入輸出關系具有非線性特徵。據此，本文提出離線建模的和在線建模的智能旋翼頻域神經控制方法，並給出實現的具體方案細節。
  7. The meijiayi mjy channels therapeutic apparatus developed by our company, combines the advanced microcomputer technics with the profound traditional chinese medicine methods as well s the human channelss science, magically takes advantages of modern electronic technics and the outer treatment of chinese medicine, realistically simulated the effects like acupuncture, aprapathy, essage, eating, kin scraping and cupping, etc. which improve the comprehensive effects, especially for the common ailments and geriatric diseases in digest digestive system, respiratory system and nervous system

    旋翼式多流束濕式基表，雙脈沖采樣方式進行數據採集，採用計算機技術進行數據處理顯示控制閥門動作。它採用獨特的卡口安全及保護措施動態安全可靠的ic卡加密機制先進的硬體及軟體的容錯處理性能安全可靠，具有精度高自身功耗低體積小壽命長便於安裝等特點。能準確實現用水計量及實現預付費功能。
  8. Numerical simulations demonstrate that the multi body analytical model can analyze the aeroelastic stability of the tiltrotor aircraft in the helicopter mode

    數值計算表明：建立的多體動力學模型能夠快速分析直升機模式下傾轉旋翼機復雜的旋翼機翼氣彈耦合動力學特性。
  9. Multi body dynamic differential equations are combined with the equations of the unsteady dynamic inflow model to establish the complete unsteadily aeroelastic coupling analytical model of the tiltrotor

    結合動力人流，研究了直升機模式下傾轉旋翼機非線性非定常氣彈耦合動力學特性。
  10. Based on the mechanism of slipstream interaction, described in this thesis is firstly the interaction of the propeller slipstream with the wing 、 fuselage and horizontal tail. subsequently, the changes in lift 、 drag and pitching moment are derived, giving an engineering model for the prediction of the increments in the aerodynamic characteristics caused by the interference between the propeller slipstream and the other parts of aircraft. this method offers a powerful means to the calculation of the aerodynamic interaction between the propeller and the aircraft, providing reliable data for the design of and aerodynamic calculation on propeller - powered aircraft

    本文以滑流干擾的機理為出發點，研究了螺旋槳滑流與飛機機翼、機身、平尾組合體之間的相互影響，推導出滑流引起的飛機升力、阻力和俯仰力矩的變化，給出了滑流干擾對機體氣動特性影響的工程估算方法，為研究螺旋槳與飛機部件之間的相互干擾提供了有力的工具，為以螺旋槳發動機為動力的飛機的設計和氣動計算提供可靠的依據。
  11. The effects of the slipstream boundary are solved by the slipstream boundary condition met using the so - called vortex image method. based on these considerations, the change in the circulation around the wing is obtained, and the velocities induced by the original vortices and the imaged vortices at the wing are subsequently derived. the present research also gives an analytical expression of the drag change due to the slipstream interference

    對于滑流邊界的影響，用「鏡像法」來使滑流邊界條件得到滿足，導出了由於滑流影響機翼環量的改變，求得渦及其鏡像在機翼處的誘導，並首次導出了螺旋槳滑流對機翼阻力特性的影響的解析表達式。
  12. During the procedure, the airspeed continues accelerating ( or decreasing ) and the aircraft configuration is rapidly changing. the aerodynamic interactions are complex and lead to dynamic instabilities. the shift between helicopter and airplane flight modes necessitates a change in control strategy

    過渡模式下，飛機速度不斷增加（或減小） ，氣動布局不斷改變，飛機動力穩定性差且氣動干擾嚴重，直升機控制和固定翼控制切換，因此過渡模式動力學特性和控制系統研究是整個傾轉旋翼飛機研製的主要難點。
  13. Along with development of tiltrotor vehicle ’ s research some theoretical productions have been appeared in some project ( aerodynamic behavior of rotor, kinetic behavior of rotor, rotor / wing aerodynamic interactions, etc. ). in order to carry on further research and experimentation of these project, national - defence science and technology helicopter rotor kinetic lab of our school begin to building tiltrotor model bench. base on need of this bench, this paper study / design pitch control system on it

    隨著對傾轉旋翼飛行器的深入研究，傾轉旋翼的氣動特性、動力學特性、旋翼/機身間的氣動干擾等課題方面已有一定的理論成果出現。為了對這些課題進行深入研究和試驗驗證，我校直升機旋翼動力學國防科技重點實驗室著手建造了傾轉旋翼模型實驗臺。
  14. 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。
  15. Combined with blade element theory, the results can be used to evaluate aerodynamic characteristics of flapping wings, which are helpful for the initial design of micro rotary and flapping wing

    運用本文方法分析了各參數對翼型氣動特性的影響，進一步結合葉素理論還可以估算撲翼的氣動特性，進而指導微旋翼或撲翼微型飛行器的初期設計。
  16. Second, taking the characteristics of the mrfd and its matching with blades into consideration, the squeeze mode mrfd was designed. after that, the mechanical characteristics of the squeeze mode mrfd was tested to tell us that, compared with those mrfd work in other modes, the squeeze mode is advantageous for its compact structure, less displacement and higher strength. third, with the test data, we get the force model which use imitatation

    其次，考慮磁流變阻尼器自身特點與直升機旋翼的匹配因素，設計了以擠壓模式為工作方式的磁流變減擺器，並對磁流變減擺器進行了力學特性試驗，試驗結果表明擠壓式磁流變阻尼器與其他工作模式的磁流變阻尼器相比具有結構緊湊、位移小、出力大等優點。
  17. Because of the special structure of smart rotor, the problem, online secondary path modeling, should be solved when adaptive filter is used to actively control the helicopter vibration. auxiliary random noise is one of the resolve methods

    出於智能旋翼結構的特殊性，在應用自適應濾波的方法進行主動控制時須解決次級通道在線建模問題。
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