NDLI: Frequency response of an aircraft wing with discrete source damage using equivalent plate analysis

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Frequency response of an aircraft wing with discrete source damage using equivalent plate analysis

Content Provider	NASA Technical Reports Server (NTRS)
Author	Krishnamurthy, T. Eldred, Lloyd B.
Copyright Year	2007
Description	An equivalent plate procedure is developed to provide a computationally efficient means of matching the stiffness and frequencies of flight vehicle wing structures for prescribed loading conditions. Several new approaches are proposed and studied to match the stiffness and first five natural frequencies of the two reference models with and without damage. One approach divides the candidate reference plate into multiple zones in which stiffness and mass can be varied using a variety of materials including aluminum, graphite-epoxy, and foam-core graphite-epoxy sandwiches. Another approach places point masses along the edge of the stiffness-matched plate to tune the natural frequencies. Both approaches are successful at matching the stiffness and natural frequencies of the reference plates and provide useful insight into determination of crucial features in equivalent plate models of aircraft wing structures.
File Size	536147
Page Count	18
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20070018865
Archival Resource Key	ark:/13960/t3518zx45
Language	English
Publisher Date	2007-04-23
Access Restriction	Open
Subject Keyword	Aircraft Design, Testing And Performance Panels Damage Assessment Aluminum Modal Response Mechanical Properties Dynamic Loads Foams Finite Element Method Wings Plates Structural Members Graphite-epoxy Composites Mathematical Models Frequency Response Stiffness Discrete Functions Aircraft Structures Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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