wing element 中文意思是什麼
wing element
解釋
機翼構件-
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。 -
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。 -
Many test cases are calculated to verify the above study. the cases are either real or standard testing models, including multi - element airfoil, wing - body configuration, cone / cylinder missile model and 3 - d high - lift systems, etc. the results of present calculation are in good agreement with experiment data, and show flexibility and accuracy of the approaches. base on the cartesian grids, this thesis has targeted the development and integration of many algorithms and techniques such as adaptive refinement, omni - tree data structure, hybrid grid method, etc. an analysis software and research methods are designed and developed for the steady - unsteady and viscous - inviscid flow complex systems and configuration
7 .運用上述研究成果和結論，進行了大量算例的實驗驗證，外形范圍包括多種標模與型號，涉及多段翼型、 m6機翼、細長體模型、翼身組合體、兩段機翼增升標模、帶縫翼和襟翼的三段增升翼身組合體等復雜外形，計算結果均與實驗吻合良好，充分說明了本文發展的各種演算法、流場求解、網格生成方法的正確性和魯棒性。 -
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。 -
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。 -
Combined with blade element theory, the results can be used to evaluate aerodynamic characteristics of flapping wings, which are helpful for the initial design of micro rotary and flapping wing
運用本文方法分析了各參數對翼型氣動特性的影響，進一步結合葉素理論還可以估算撲翼的氣動特性，進而指導微旋翼或撲翼微型飛行器的初期設計。 -
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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