振動翼 的英文怎麼說

中文拼音 [zhèndòngyì]
振動翼 英文
oscillating airfoil
  • 振 : 動詞1. （搖動; 揮動） shake; flap; wield 2. （奮起） brace up; rise with force and spirit
  • 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...
  • 振動 : vibrate; vibration; vibrance; vibrancy; vibra; vibes; shaking; rumble; jitter; chatter; sway; jar...
  1. In order to prove the feasibility of the control method mentioned, both the semiphysical test for the plant simulated by analogue computer and the model test for the cantilever beam are designed and finished with the study of the parameter selection in realization

    對離線建模的智能旋翼頻域神經控制方法進行了試驗驗證研究，試驗分兩種情況：以模擬計算機模擬受控對象的半物理模擬試驗與懸臂梁振動響應控制試驗，並研究了實現中的參數選擇問題。
  2. The active vibration control aimed at aircraft empennage has huge practical values in the aspects of adding the fatigue life of vertical tail, increasing the capability and availability of the aircraft, reducing the through - life - support costs and so on

    飛行器垂直尾翼的振動主動控制對于提高尾翼的疲勞壽命、飛行器的機動性以及減小飛行器的維護成本具有較大的實際意義。
  3. Splits, spread eagles, back flips, flip flops

    張翼，大鵬展翅，往後振翅，不斷拍動
  4. The smart rotor with active trailing edge is a new system for reducing the vibration which can adjust the air load of the blade to actively counteract the main harmonic of the force to the fuselage by controlling the deflection of the trailing edge

    主動后緣附翼控制是一種較新的旋翼減振系統，它通過控制后緣附翼的偏轉，調節槳葉的氣動載荷，實現對機體激振力主要諧波分量的主動抵消。
  5. 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。
  6. In today ? service economy and service society ; as to airline who hoping to keep eternally continuous development, to maximize customer satisfaction shal

    不重視它猶如在蒸汽機車、馬車上前進，而不是振翼高飛。時不我待，航空公司應該堅決迅速地行動起來。
  7. This thesis, which is devoted to the research on the smart rotor with actively controlled trailing - edge flap for hub oscillatory load reduction, offers a potential approach for the vibration reduction of helicopter

    本文對帶有主動控制后緣附翼的智能旋翼用於降低槳轂交變載荷進行探索性的研究，為降低直升機飛行中機體振動水平提供一條有效的新途徑。
  8. This deforming method coupled with ale euler solver is applied to simulate unsteady transonic flow about oscillating airfoil ( 2 - d ) and oscillating rigid rectangular wing ( 3 - d ). computational results are in good agreement with experimental data

    本文將網格變形方法與數值解算器耦合起來求解了二維振動翼型繞流和三維振動矩形機翼繞流，計算結果與實驗結果一致，證明本文的數值方法具有較高的準確性。
  9. This dissertation presents how to use the ultrasonic motor as an actuator to suppress the flutter of a two - dimensional airfoil section with a control surface. the ultrasonic motor, which features simple structure, high torque at low speed, small size, low weight and no electromagnetic contamination, is a promising actuator for the flutter suppression of small aircraft

    超聲電機以其結構簡單緊湊、轉矩/質量比大、低速大扭矩、直接驅動，動態響應快、斷電自鎖和不產生磁場且不受外界磁場干擾等優點，有望成為一種非常有前途的作動器，用於小型飛機的機翼顫振主動抑制。
  10. Firstly, the airfoil ' s classic flutter ( at small attack angle ), stall flutter ( near the static stall angle ) and response ( at large attack angle ) are analyzed. it is found from the numerical results that " lock - in " will occur at certain freestream velocity range near the static stall angle, where the frequency of the vortex will be equal to the natural frequency and the flutter has the characteristic of self - induced oscillation. when the attack angle is far from the static stall angle, the vortex will have its own frequency, which differs from the natural frequency, and the flutter has the characteristic of forced oscillation

    首先研究了二維翼型的古典顫振（小攻角） 、失速顫振（失速攻角）和動力響應問題（大攻角） ，得到以下結論：在靜態失速攻角附近的一定來流速度范圍內，分離渦會發生頻率鎖定現象，分離流的頻率與固有頻率趨于相同，這時的振動呈現自激振動的特點；遠離失速攻角時分離流頻率則擺脫固有頻率的影響，此時的振動具有強迫振動的特點。
  11. Thirdly, in term of the results of testing and calculation, the displacement and libration, the difference of altitude, the flexibility and strain of crane - beams are all generally analysed, especially the reason why the crane - beams are attaint is lucubrated, and the reasons why the trigging pole is ruptured, the upper wingspan is damaged, the orbital movement, the exceptional incline of colums are open out, which has instructional significances that improve the design of the steel frame of the coke made by dry flameout

    第三，根據檢測和計算結果，對鋼框架的位移和振動、框架高差、吊車梁撓度和應變等進行了全面的分析，特別對吊車梁系統的損傷原因進行了深入分析，揭示了制動桿件斷裂、上翼緣磨損、軌道竄動、柱異常傾斜等一系列損傷現象的原因，對于改進干熄焦鋼框架的設計有著直接的指導意義。
  12. To study the acoustic unsteady combustion of srm, built the acoustic model of chamber. deduced the little amplitude sound wave 3d equation, used the finite volume discrete method to simulate. got the vibration model of three kinds of chamber

    為研究固體火箭發動機聲不穩定燃燒特性，建立了燃燒室內聲學特性分析的物理數學模型，推導了小振幅聲波三維波動方程，採用有限體積離散方法進行模擬，得到圓柱型、四片翼柱彤和五片翼柱型藥柱三種燃燒室形狀聲學振動基本模態
  13. Finally, the 2d unsteady navier - stokes flow solver is coupled with two - degree - of - freedom flutter motion equation in time domain to investigate the flutter characteristics of several supercritical airfoils

    最後，本文將二維非定常nayier - stokes方程解算器與顫振運動方程耦合，研究了超臨界翼型的跨音速顫振特性。
  14. But in many cases, vibration is harmful and could affect the user ' s comfort, even cause giant safe accidents. for examplethe vibration of the wings of a plane in the airflow effect and the vibration of the running cars in the road effect, and so on

    但在許多情況下，振動是有害的，如飛機機翼在氣流作用下的振動、行駛的汽車在路面作用下的振動等等，它們都會影響到使用的舒適性，嚴重時甚至造成重大安全事故。
  15. As a new type of active vibration control for helicopter, the smart rotor is a hot point in the field of helicopter engineering

    作為一種新的直升機振動主動控制形式，智能旋翼成為目前直升機工程界的一個研究熱點。
  16. 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。
  17. In the transversal vibration test of the steel supporting post on the flange of qinshen railway bridge, the practical techniques of instrument selection, the provision of static eliminater and the way of data sampling are mainly discussed

    摘要針對秦沈線橋上翼緣板接觸網鋼柱的橫向振動測試，著重論述了儀器的選型、抗靜電干擾措施以及數據採集中的具體技術。
  18. Coupled buffeting analysis of long span bridges with stationary aerodynamic wings

    安裝固定氣動翼板的大跨橋梁抖振分析
  19. The vibration and sound radiation behaviors of the stem of submarine with rudder and vane are studied

    摘要針對帶有舵翼的水下航行器尾部結構模型，研究舵翼對水下航行器尾部的振動及聲輻射的影響。
  20. This paper aims at model of vertical tail based on certain type aircraft. the method of distributed actively vibration control based on multi dsp has been carried on this model. a distributed actively vibration control system based on dsps is designed to real timely control the structural vibration of two modes

    本文以某型飛機的尾翼模型為目標，採用基於多dsp處理器的分散式控制方法實現對垂直尾翼模型的振動主動控制，開發出了一套基於dsp的振動主動控制系統，針對結構的兩階模態振動實施了分散式振動主動控制，並進行了相關的理論和實驗研究。
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