finite wing 中文意思是什麼

finite wing 解釋
有限翼板
  • finite : adj. 有限的；【語法】限定的；【數學】有窮的，有盡的。n. 〈the finite〉 有限（性）； 〈集合詞〉有限物。adv. -ly ,-ness n.
  • wing : n 1 翼，翅膀；鳥；鳥群；飛行，飛翔。2 （飛機）機翼；翼狀物；（汽車的）擋泥板；〈詩常 pl 〉船帆。3...
  1. The wing is modeled structurally by vibrational modes, which are used as amplitude of motion by a finite element analysis. conservative full - potential equation and three dimensional unsteady euler equation are used to compute the unsteady transonic flows around airfoil and wings under simple harmonic motion

    以給定機翼模態分佈下機翼上各點的模態值作為運動幅值，以三維非定常全位勢方程和三維非定常euler方程為控制方程，求解三維機翼簡諧運動下的非定常氣動力。
  2. First, the repeated structural analyses for static and dynamic characteristics are needed in the integrated optimization of composite wing structures. in this situation, the finite element model ( fem ) is time - consuming, while the continuum equivalent plate model ( epm ) is more efficient and often used

    首先，復合材料翼面結構綜合優化設計需要反復進行結構靜力和動力特性分析，如果採用有限元模型（ finiteelementmodel ，簡稱fem ） ，則其工作量太大。
  3. The research of this dissertation is focused on how to solve the 3 - dimensional compressible navier - stokes equations by the implicit finite difference algorithm and to simulate numerically the unsteady subsonic and transonic viscous flows around rigid and elastic wings. on the base of them the aeroelastic characterictics of an elastic wing have been studied

    本文的主要工作是用隱式有限差分法求解三維非定常紊流n - s方程組，數值模擬剛性機翼及彈性機翼的亞、跨、超音速定常及非定常粘性繞流，並在此基礎上研究了彈性機翼的氣動彈性問題。
  4. The surface finite element solver brought forward by woodward is improved. according to the improved solver, the interfere between bomb and plane is researched. the aerodynamic parameters of the bomb, which under the wing are calculated

    本文對伍德沃德提出的面元法加以改進，並應用改進后的面元法對航彈機彈干擾進行了研究。
  5. Several non - linear phenomena are also analyzed. by using uncoupled thermal - structure analyzing method, with the consideration the additional stiffness caused by thermal stress, the finite element model for thermal - vibration analysis is obtained and two typical hypersonic wing structures are computed

    運用非耦合熱-結構分析方法，考慮熱應力引起的附加剛度，得到熱環境下的結構分析的有限元模型，並計算了兩種典型結構的高超音速翼面熱結構。
  6. The model is solved with the finite difference method, the simulation software is organized to simulate the transient thermal response of the front region of projectile wing such as those launched by electrothermal chemical guns

    採用有限差分法進行數值求解，並編制了較為通用的模擬軟體，用於模擬諸如由電熱化學炮發射的高超聲速穿甲彈彈翼前緣的瞬時熱效應。
  7. In this thesis, finite volume method and dual - time stepping method are employed to solve the 3 - d unsteady euler equations. the unsteady flow field around a finite - span flapping wing is simulated. the lift and thrust of the flapping wing for different cases are calculated

    本文運用有限體積法結合雙時間推進技術求解三維非定常歐拉方程，模擬了有限翼展機翼在同時具有上下拍動和俯仰運動狀態下的非定常流場，計算了不同狀態下撲翼的升力及推力，分析了各個影響因素對撲翼氣動特性的影響。
  8. Combined with modem structural finite element analysis, modern structural optimization algorithms, composite structures mechanics and aeroelastic tailoring of composite wing as well as relative high performance numerical method, a system named the composite synthesis optimization for aircraft structures ( cosoas ), has been developed in this paper, which has own independent component of finite element analysis

    本文結合現代結構有限元分析方法、現代結構優化演算法、復合材料結構力學、復合材料氣動彈性剪裁設計方法以及相關的高性能數值計算工具開發出了擁有自己獨立有限元程序的復合材料飛機結構綜合優化設計系統（ cosoas ） 。在內容上本文突出復合材料應用特色。
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