顫振速度 的英文怎麼說

中文拼音 [zhànzhènsùdù]
顫振速度 英文
flutter speed
  • 顫 : 顫動詞（發抖） shiver; shudder; tremble
  • 振 : 動詞1. （搖動; 揮動） shake; flap; wield 2. （奮起） brace up; rise with force and spirit
  • 速 : Ⅰ形容詞（迅速; 快） fast; rapid; quick; speedy Ⅱ名詞1 （速度） speed; velocity 2 （姓氏） a surna...
  • 度 : 度動詞[書面語] （推測; 估計） surmise; estimate
  • 速度 : 1. [物理學] velocity; speed; blast; bat 2. [音樂] tempo3. （快慢的程度） speed; rate; pace; tempo
  1. But jonathan livingston seagull, unashamed, stretching his wings again in that trembling hard curve … slowing, slowing, and stalling once more … was no ordinary bird

    但岳納珊不是平凡的海鷗，他並不感到羞愧，反而重新振翼，再彎成顫抖不穩的弧形? ?放慢速度、再放慢，又失速墜落。
  2. To a series of dampings, velocities and frequencies, the linear interpolation is applied and the flutter speed and flutter frequency are obtained

    對得到的一系列的阻尼、速度和頻率進行了線性插值，從而得到顫振速度和顫振頻率。
  3. At first, the finite element formulation is presented to determine the flutter characteristics of laminated panels at elevated temperature. then both the linear and nonlinear panel flutter characteristics are analyzed. the panel flutter boundaries are finally determined and the effect of temperature, airflow speed, etc, on the panel flutter characteristics is analyzed

    為此，本文首先建立了復合材料壁板熱顫振的有限元模型並對受熱壁板的線性和非線性顫振特性進行了研究；最後確定了壁板的顫振邊界，分析了溫度、來流速度等因素對壁板顫振特性的影響規律。
  4. 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。
  5. Then the steady and unsteady subsonic, transonic and supersonic viscous flows around airfoil and some aircraft are numerically simulated. the 3 - dimensional unsteady navier - stokes equations are solved using the implicit lu - nnd algorithm, with baldwin - lomax turbulent model. on the basis of simulating unsteady viscous flow, coupling the structure dynamics equations, the problems of static aeroelasticity and flutter are investigated for wings and elevator

    在模擬非定常粘性繞流的基礎上，與顫振運動方程相耦合，分別對機翼和全機流固耦合現象中顫振問題進行了研究，準確求解跨音速顫振臨界速度，分析機翼和全機的從亞音速到超音速范圍的顫振規律，並研究分析了機翼飛行迎角變化對顫振速度的影響。
  6. The nonlinear panel flutter equations are also solved in time domain. the limit cycle flutter characteristics of nonlinear panel flutter are investigated and the effect of temperature and airflow speed on the nonlinear panel flutter characteristics is studied

    通過對非線性壁板顫振方程的時域求解，研究了壁板的極限環顫振特性，得到了溫度、氣流速度等因素對非線性壁板顫振特性的影響規律。
  7. A linear saturated law is used to restrain flutter. the critical velocity can be improved more than 30 %

    實現了顫振的主動抑制，可以將原有氣動彈性系統的臨界速度提高30以上。
  8. In chapter 4, the aeroelastic model of the whole test rig is first established by using jones ’ s approximation of theodorsen ’ s unsteady aerodynamics load. then, the numerical simulations and wind tunnel experiments for the sub - optimal flutter suppression of the airfoil model are presented

    數值模擬和風洞實驗研究表明，以超聲電機為控制面作動器可以有效地抑制翼段模型的顫振，顫振臨界速度提高了13 . 4 % ，數值模擬和風洞實驗結果基本吻合。
  9. The investigation in this dissertation shows the capabilities of ausm + scheme, such as the exact resolution of shock, low numerical dissipation, simple and requiring less computational effort. the successful applications on supercritical airfoils and wings show that the present flow solvers based on ausm + scheme are of valuable and promising in practical application

    通過本文的研究工作，展示了ausm +格式的激波高解析度、數值耗散小、編程簡潔、計算量較小等特性，同時，將其成功地應用於跨音速超臨界翼型、機翼的定常或非定常氣動特性的數值模擬和顫振研究中，具有一定的工程應用價值和良好的發展前景。
  10. Both h controller and synthesis are designed when the damping uncertainties in plunge

    在稍大於顫振臨界速度的風
  11. The numerical simulations agree well with the wind the tunnel experiments, and the critical speed is increased by 13. 4 %. chapter 5 presents the robust flutter suppression of the airfoil

    數值模擬和風洞實驗表明，這兩種控制器是有效的，可將系統的顫振臨界速度提高23 . 4 % 。
  12. Numerical results are in good agreement with some data and the method and procedure presented in this paper are verified. and then the wing ? flutter characters of a missile wing are numerical simulated with the examples of a missile wing

    以某導彈翼面為算例，對彈翼的亞、跨、超音速的顫振臨界速度進行了數值計算，部分計算結果與風洞計算結果相比較，一致性很好。
  13. Apart from the mathematical properties of the dirac operator we investigate the behavior of observables such as position, velocity, momentum, describe the zitterbewegung, and formulate the localization problem

    除了狄拉克運算元的數學工具之外，我們研究諸如位置，速度，動量等看得見的客觀屬性，描述了顫振，並闡述一些局部問題。
  14. In addition, aerodynamic stiffness and aerodynamic damping on the system are already obtained in the condition of fluid - structure interaction. it is known that aerodynamic loads are associated with blade vibration. the systematic eigenvalues are used to judge whether the flutter occurs so as to find the stable operating range of a wind turbine

    本文把風力機葉片簡化為懸臂梁，對梁截面的二維葉型建模，完整推導了二維葉型的線性運動微分方程和流構耦合條件下系統的氣動剛度和氣動阻尼，此時氣動載荷與結構的位移矢量以及速度矢量是相互耦合的，再利用系統的特徵值來判斷葉片顫振是否發生，從而獲得風機的穩定工作范圍。
分享友人
分享到 Line

分享到臉書