Dynamic Aeroelasticity of Structurally Nonlinear Configurations Using Linear Modally Reduced Aerodynamic Generalized Forces
Dynamic Aeroelasticity of Structurally Nonlinear Configurations Using Linear Modally Reduced Aerodynamic Generalized Forces
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DOI：
10.2514/1.34797
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发表时间：
2007-04
期刊：
影响因子：
2.5
通讯作者：
L. Demasi;E. Livne
中科院分区：
文献类型：
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作者：
L. Demasi;E. Livne
针对具有几何非线性的结构，介绍了基于模态法和全阶浮体单元模型的常用频域非定常气动建模的定常方法和时间域方法。这种方法是针对几何刚度很重要但变形适中、附加∞ow且线性非定常气动模型足够的飞机火灾，如小到中攻角的连接机翼和支撑机翼或小展弦比机翼。用全阶非线性结构模型和全阶气动模型(包括所有气动壁板的∞气动系数)得到的结果与用模态法得到的广义气动矩阵的全阶结构模型的结果进行了比较。
Steady state and time domain methods for integrating commonly used frequency-domain unsteady aerodynamic modeling based on a modal approach with full order flnite element models for structures with geometric nonlinearities are introduced. The methods are aimed at airplane conflgurations where geometric stifiness efiects are important but where deformations are moderate, ∞ow is attached, and linear unsteady aerodynamic modeling is adequate, such as joined-wing and strut-braced wings at small to moderate angles of attack or low aspect ratio wing. Results obtained using full order nonlinear structural modeling and full order aerodynamic modeling (including aerodynamic in∞uence coe‐cients for all aerodynamic panels) are compared to results obtained using full order structural modeling with generalized aerodynamic matrices obtained using a modal approach.