Finite element model development for aircraft fuselage structures

被引：0
|
作者：
Buehrle, Ralph D. [1 ]
Fleming, Gary A. [1 ]
Pappa, Richard S. [1 ]
Grosveld, Ferdinand W. [2 ]
机构：
[1] NASA Langley Research Center, Hampton, VA, United States
[2] Lockheed Martin Eng. and Sciences, Hampton, VA, United States
来源：
S V Sound and Vibration | 2001年 / 35卷 / 01期
关键词：
Acoustic variables control - Algorithms - Aluminum - Beams and girders - Computer simulation - Finite element method - Fuselages - Modal analysis - Plates (structural components) - Shells (structures) - Structural analysis - Structural frames;
D O I：
暂无
中图分类号：
学科分类号：
摘要：
The ability to extend the valid frequency range for finite element based structural dynamic predictions using detailed models of the structural components and attachment interfaces is examined for several stiffened aircraft fuselage structures. This extended dynamic prediction capability is needed for the integration of mid-frequency noise control technology. Beam, plate and solid element models of the stiffener components are evaluated. Attachment models between the stiffener and panel skin range from a line along the rivets of the physical structure to a constraint over the entire contact surface. The finite element models are validated using experimental modal analysis results.
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页码：32 / 38
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