NDLI: Behavior of frame-stiffened composite panels with damage

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Behavior of frame-stiffened composite panels with damage

Content Provider	NASA Technical Reports Server (NTRS)
Author	Jegley, Dawn C.
Copyright Year	2013
Description	NASA, the Air Force Research Laboratory and The Boeing Company have worked to develop new low-cost, light-weight composite structures for aircraft. A Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept has been developed which offers advantages over traditional metallic structures. In this concept, a stitched carbon-epoxy material system has been developed with the potential for reducing the weight and cost of transport aircraft structure by eliminating fasteners, thereby reducing part count and labor. Stitching and the use of thin skins with rod-stiffeners to move loading away from the morevulnerable outer surface produces a structurally efficient, damage tolerant design. This study focuses on the behavior of PRSEUS panels loaded in the frame direction and subjected to severe damage in the form of a severed central frame in a three-frame panel. Experimental results for a pristine two-frame panel and analytical predictions for pristine two-frame and three-frame panels as well as damaged three-frame panels are described.
File Size	15625513
Page Count	13
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20130012914
Archival Resource Key	ark:/13960/t1vf1tp8f
Language	English
Publisher Date	2013-04-08
Access Restriction	Open
Subject Keyword	Composite Materials Panels Frames Epoxy Matrix Composites Transport Aircraft Weight Reduction Durability Military Technology Rods Pultrusion 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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