翼上旋翼 的英文怎麼說

中文拼音 [yìshàngxuányì]
翼上旋翼 英文
wing-mounted rotor
  • 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...
  • 上 : 上名詞[語言學] （指上聲） falling-rising tone
  • 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...
  • 旋翼 : helicopter rotor
  1. Breakthroughs in modern gyroplane technology - an introduction to the advances in gyroplane technology and the emerging market opportunities for a new generation of gyroplanes ranging from small vtol & ustol gyroplanes to large vtol gyrodyne airliners or freighters with 20 ton payload capacity

    現代旋翼機科技的突破-介紹旋科技的進步，以及新一代旋翼機的市場機會，從小型超短距離升降和垂直升降的旋翼機到可垂直升降，載重20噸以上的大型直升旋翼客機和貨運機
  2. A board on a paddle wheel

    明輪翼螺旋槳上的寬闊葉板
  3. Handling loads suspended from rotorcraft

    裝卸旋翼機上懸吊的貨物
  4. With additional capabilities in rotorcraft, electronic and defense systems, missiles, rocket engines, satellites, launch vehicles and advanced information and communication systems, the company ' s reach extends to customers in 145 countries

    加上旋翼飛機、電子和防禦系統、導彈、火箭發動機、衛星、運載火箭和先進信息及通訊系統等方面的研製能力，本公司的客戶已經遍及145個國家。
  5. When the tilt rotor vehicle is in hover, the aerodynamic download of the rotor flowfield imposes on the wing. in this time, the rotor / wing interaction is severe

    傾轉旋翼飛行器懸停時，旋翼的下洗流剛好作用在機翼上，此時，旋翼機翼間的氣動干擾非常劇烈。
  6. The two astazou turboprops are mounted in slender nacelles in the leading edges of the wings and drive three - blade propellers

    兩臺發動機安裝在機翼上小巧的發動機艙內，各驅動一個三葉螺旋槳。
  7. On the basis of axial vortex theory, the aerodynamic performance of tilt - rotor model has been built, and using it to analyze the aerodynamic performance of xv - 15, comparing to the actual data to prove the model ’ s validity, finally studied the variety of aerodynamic performance relative to the variable rotor diameter

    以軸向渦流理論為基礎，建立了適合於傾轉旋翼機氣動分析模型，以xv - 15傾轉旋翼機作為算例，通過結果的對比，表明本文的氣動模型能較好的分析傾轉旋翼機的氣動性能，並在氣動性能的基礎上分析了直徑變化對傾轉旋翼機氣動性能的影響。
  8. 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。
  9. In order to analyze this model, a modified multi - blade coordinate transformation was proposed. at last, the aeromechanical stability problem was analyzed with the two

    最後用上述兩種分析方法對帶葉間減擺器的旋翼/機體耦合系統的氣動機械穩定性問題進行了分析研究。
  10. 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翼動態尾跡模型，使用該模型對傾轉旋翼機傾轉過渡狀態的尾跡彎曲變形進行了研究，得出了一些結論。
  11. And a pair of flaps, mounted on the stern stabilizers, enables the vehicle dive or surface in a spiral form, thus ensuring the vehicle almost directly under the support ship

    在潛水器的尾部穩定翼上裝有一對小襟翼，它可使潛水器在上浮下潛時，在母船的正下方作螺旋狀盤旋。
  12. This setting could increase the damping of angular rates and improve the stability. based on bell stabilizer bar, bell - hiller stabilizer bar adds small wing on the two ends of bar. compared with main blades the aerodynamic forces and moments generated by the bar could be neglected

    希勒伺服旋翼在貝爾穩定桿的基礎上，于兩個質量塊處添加了小翼，與貝爾穩定桿相比，希勒伺服旋翼自身的揮舞運動藉助機械耦合引起旋翼二次變距，起到改善操縱性的作用。
  13. 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。
  14. The paper introduces the structure of helicopter airscrew loading system and constructs the mathematical model of single channel loading system and analyses its dynamic performance

    論文介紹了直升機旋翼加載系統的結構，在建立了單通道加載系統的數學模型的基礎上，分析了加載系統的動態性能。
  15. 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。
  16. At last, pointing to the temporal characteristics and the spectral characteristics, this paper discussed the methods for estimating the maximal line velocity ( vmax ) and the glint periods ( tp ) of the hovering helicopter, and then fulfilled the recognition of hovering helicopter using these two message. in chapter 5, the summary of all the works in the paper and related conlusions are presented, and the defects are analized at last, at last this paper demonstrated the d

    最後，本文針對懸停直升機旋翼回波的時頻域特點，探討了從回波信號中提取旋翼回波最大線速度v和旋翼回波閃爍周期tp的方法，在綜合利用這兩種信息的基礎上完成了彈載高重頻脈沖多普勒體制雷達對懸停直升機回波信號的識別。
  17. The superposition between the helicopter rotor induced flow and the warship airwake leads to the formation of the complex wake, which affects the helicopter ' s control response and flight safety during take - off and landing from a warship

    摘要直升機旋翼誘導流與艦船空氣尾流疊加后形成復合流場，對直升機艦上起降時的操縱響應及飛行安全有很大的影響。
  18. Included three positions system, the helicopter airscrew electro - hydraulic servo loading system has coupling nexus of three positions and three loadings. trough analyzing nexus of the displacement and the force, this paper designs the three channels electro - hydraulic servo loading system basing on the analysis of single channel electro - hydraulic servo loading system. surplus torque, which is produced through position disturbance, is a chief problem facing aerodynamic loading system

    直升機旋翼的操控通過三個助力器完成，模擬負載時把旋翼所受空氣動力折算到了三個助力器上，由於三個助力器是鉸點在一個模擬盤上，所以三通道加載系統與三個助力器位置系統有一定的耦合關系。
  19. Abstract : the radar echo of a helicopter rotor is modeled and analyzed theoretically at first, then a new method is proposed to detect hovering helicopter by using low - pass filter and multilevel hypothesis examination

    文摘:首先對直升機旋翼的雷達回波進行建模和分析，在此基礎上提出一種懸停直升機積累檢測新方法即低通濾波和多級假設檢驗相結合的方法。
  20. The communication protocol between host computer and lower computer is showed. the watch and control software is designed using c + + language. this software can realized these function : system self - check, system initialization, rotor pitch control, display and save of transform matrix, document print etc

    對上、下位機通信協議作了分析，用面向對象設計的c + +語言編寫了整個系統的監控軟體，主要實現了系統的自檢、初始化，旋翼槳距的控制，變換矩陣和實驗數據的顯示、存儲和列印等功能。
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