飛機動力學 的英文怎麼說

中文拼音 [fēijīdònglìxué]
飛機動力學 英文
aircraft dynamics
  • 飛 : Ⅰ動詞1 （鳥、蟲等在空中活動） fly; flit 2 （利用動力機械在空中行動） fly 3 （在空中飄浮遊動） fly...
  • 機 : machineengine
  • 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...
  • 飛機 : airplane; plane; aeroplane; kite; bird; aircraft
  1. A three - dimensional rigid body model is used to study the landing of a helicopter in autorotation

    首先，建立了一個描述直升機自轉著陸飛行動力學特性的三維剛性體模型。
  2. 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。
  3. 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。
  4. As to the modelling of integrated flight / propulsion system, this paper mainly investigated and the modelling methods of flight kinetics and propulsion system thermodynamics, building up the real - time models of body kinetics. then we integrated the component - level thermodynamics model of engine, solved the problem of matching of initial points in the integrated simulation of flight / engine and the interactive parts of flight system and propulsion system

    對于綜合飛行/推進系統建模，本文主要研究的是飛行動力學和推進系統熱力學的建模方法，建立了飛機動力學實時模擬模型。並結合前人已建立的發動機部件級熱力學模型，本課題在解決了飛機/發動機綜合模擬中的起始點匹配問題的基礎上，完成飛行系統和推進系統的交互部分，最終建立飛行/發動機綜合實時模擬模型。
  5. Summary about inverse problem of helicopter flight dynamics

    直升機飛行動力學逆問題研究綜述
  6. The exploration of flight dynamics problem on aircraft icing

    飛機結冰引起的飛行動力學問題探討
  7. Flight dynamics - concepts, quantities and symbols - part 6 : aircraft geometry

    飛行動力學.概念量及符號.第6部分:飛機幾何參數
  8. 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。
  9. 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。
  10. Investigation of flight dynamics of thrust vectoring aircraft using extended continuation methods

    應用擴展連續演算法研究推力矢量飛機動力學特性
  11. Analysis methods and its development about effect of ice accretion on aircraft flight dynamics characteristics

    結冰對飛機動力學特性影響的分析方法及其進展
  12. Firstly, a dynamics equation is got by analyzing the aerodynamics change brought by aircraft differential tail

    首先，分析差動平尾所引起的飛機氣動力的變化，從而導出相應的飛機動力學方程。
  13. The thesis describes the conception of the object - oriented modeling and integrated simulaton enviroment, and discusses the below topics : ( 1 ) describe the reasonable structure of the modern fighter simulation system, and design the data transfer interface. ( 2 ) discuss the modeling method of the key subsystem of future fighter system especially the aerodynamics and the control system in detail. ( 3 ) construct the 3d model of the aircraft and scene, and verify the graphic simulation technique based on pc

    本文詳細討論了面向對象建模方法以及一體化模擬環境的基本概念框架及基本結構並在此基礎上提出了合理的現代戰斗機模擬系統結構，設計了模擬系統的數據傳遞介面；詳細討論了現代戰斗機模擬系統關鍵子系統? ?飛機本體、飛行控制系統建模方法；建立了用於研究的飛機以及視景的三維顯示平臺；並在此基礎上實現了實驗性的基於pc的現代戰斗機圖形模擬平臺，對模擬模型有效性確認和驗證工作做了初步的探討，研究比較了傳統飛行動力學和運動學方程和四元數法在飛行模擬中的效果。
  14. According to flight dynamics, a particle model and an attitude model in launching coordinate system and in quasi missile body coordinate system are established, the influence imposed by constant wind, thrust bias of the motor and connection bias are analyzed

    應用飛行動力學理論，建立了發射坐標系與準彈體系下助推段和分離過程質點運動和姿態動力學模型，分析常風干擾、發動機推力偏差和裝配誤差影響等。
  15. 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。
  16. With the development of simulation - technology and virtual reality, virtual prototype based on system simulation, flight dynamics, electronic technique, autocontrol theory and cad / cam has been more and more widely applied to the military rehearsal and the design and manufactural process of major weapon system

    隨著模擬技術特別是虛擬現實技術的發展，以系統模擬、飛行動力學、電子技術、自動控制理論以及cad cam技術等為基礎的虛擬樣機技術在大型武器系統的研製以及軍事演習等方面的應用愈加的成熟起來。
  17. The focuses of this paper are on flight environment simulation and high span - chord ratio uav model

    本文的工作就是圍繞飛行環境模擬和無人機動力學模擬展開。
  18. This model is formulated as a non - linear state - space representation of helicopter flight dynamics, incorporating with blade element unsteady aerodynamics, a finite state dynamic inflow wake model, and flapping / lead - lag blade dynamic model. the formulation of the coupled rotor and fuselage equations enables the use of common solution techniques for trim and linearization in arbitrary steady flight condition as well as control response calculations

    本項研究針對新機研製過程必須解決的品質評定、飛控系統設計等問題，按照ads - 33軍用品質規范的要求，建立了一個較完整的直升機非線性的、具有狀態空間表達形式的飛行動力學模型，進行了模型驗證工作，並以某樣例直升機為例，計算了ads - 33品質規范（ 3
  19. In follow, nonlinear six - degrees - freedom uav dynamic model is built, that is base of flight simulation. arithmetic in matlab simulation is analyzed. uav flight control law and navigation mode are given

    其次，建立了無人機從發射到傘降回收的十二階s - function非線性飛行動力學模型，並對其模擬演算法進行了分析。
  20. After establishing dynamics model of helicopter, we can design the control system for the helicopter, using the most advanced method. we can make our system gain the most excellent performance by repeating trial

    本論文對直升機增穩控制系統進行研究、利用現有的直升機動力學模型以及針對該直升機模型建立的增穩控制系統建立一套直升機機動飛行控制模擬軟體。
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