旋翼力學 的英文怎麼說

中文拼音 [xuányìlìxué]
旋翼力學 英文
rotor mechanics
  • 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...
  • 力 : Ⅰ名1 （力量; 能力） power; strength; ability; capacity 2 [物理學] （改變物體運動狀態的作用） forc...
  • 學 : Ⅰ動詞1 （學習） study; learn 2 （模仿） imitate; mimic Ⅱ名詞1 （學問） learning; knowledge 2 （學...
  • 旋翼 : helicopter rotor
  1. The stability of the tiltrotor in the heli copter mode is analyzed aiming t a semi span soft - inplane tiltrotor model with an elastic wing

    集成了非定常動態人流方程與傾轉過渡狀態的多體動力學力程，建立了傾轉旋翼機時域非定常氣彈耦合分析模型。
  2. This paper is a review of rotorcraft cfd in light of major unsolved problems, and some prospects and solution philosophy for solving them

    本報告是依據未解決的重大問題、解決這些問題的若干前景和指導思想對旋翼機計算空氣動力學（ cfd ）所作的評述。
  3. Research on the aerodynamic interaction between the rotors and components of rotorcraft have been a very important aspect and a very challenging subject in rotorcraft aerodynamics

    旋翼干擾空氣動力學問題一直是旋翼飛行器空氣動力學的研究熱點和難點之一。
  4. The model developed here is suitable for the tilt rotor aircraft during hover, transition and cruise. the longitudinal equations of motion provide a foundation for further investigation on tilt - rotor flight dynamics

    文中所建模型具有較高精度，適合於飛行包線內的所有模式，為傾轉旋翼飛機飛行動力學的進一步研究提供了基礎。
  5. 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。
  6. 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。
  7. The multi - body analysis of the aeroelastic stability of the tiltrotor aircraft is presented

    摘要通過多體動力學方法建立了傾轉旋翼機動力學分析模型。
  8. As one of the basic problem of helicopter dynamics, the aeromechanical stability of the coupled rotor - body system has been paid a lot of attention

    直升機旋翼/機體耦合系統的氣動機械動穩定性問題是直升機動力學的基本問題之一，長期以來一直受到人們的普遍關注。
  9. To study the influence of this damper configuration to aeromechanical stability, some work has been done in this thesis. first, dynamic equation of the rotor - hub system was modeled with the generalized hamilton principle, which can be used to analyze the stability problem in different conditions like on - ground, hovering and flight. when fastening the fuselage, the model can also be used to analyze the stability problem of isolated rotor system

    為了研究這種新型布置減擺器對直升機穩定性的影響，本文所作研究工作如下:首先，本文利用廣義的hamilton原理建立了適用於不同狀態（地面、懸停和前飛）的旋翼/機體耦合系統的動力學模型，該模型中將機體固定可以用來分析孤立旋翼的穩定性問題。
  10. 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。
  11. 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。
  12. 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。
  13. 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。
  14. 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。
  15. 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。
  16. 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。
  17. Based on the aerodynamics, control, structural dynamics model of smart rotor in frequency domain deduced and the determination for the number of neurons in hidden layer, the neuro - emulator using multiple independent miso neural networks with its deduced matrix expression for the smart rotor is set up. the rate of training is improved by introducing the orthogonal selection applying for smart rotor to the selection of training cases in neural modeling

    試驗結果驗證了該方法的可行性，在建立了帶有主動控制后緣附翼的智能旋翼系統氣動-控制-結構動力學數學模型的基礎上，提出了適用於智能旋翼建模的多神經網路並聯型式的頻域模型，並推導出其矩陣表達式，探討了隱含層神經元數的確定方法。
  18. 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。
  19. 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。
  20. Combining cfd technology and aeroacoustic theory in time domain, the high - speed impulsive ( hsi ) noise of helicopter rotor in hover and in forward flight was predicted and investigated

    本文結合cfd （計算流體力學）技術與氣動噪聲時域理論，求解直升機旋翼懸停和前飛流場及流場氣動噪聲。
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