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Evaluation of Long Composite StrutsCarbon-epoxy tapered struts are structurally efficient and offer opportunities for weight savings on aircraft and spacecraft structures. Seven composite struts were designed, fabricated and experimentally evaluated through uniaxial loading. The design requirements, analytical predictions and experimental results are presented. Struts with a tapered composite body and corrugated titanium end fittings successfully supported their design ultimate loads with no evidence of failure.
Document ID
20110007017
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Jegley, Dawn C. (NASA Langley Research Center Hampton, VA, United States)
Wu, K. Chauncey (NASA Langley Research Center Hampton, VA, United States)
Phelps, James E. (ATK Space Systems Hampton, VA, United States)
McKenney, Martin J. (ATK Space Systems Hampton, VA, United States)
Oremont, Leonard (Lockheed Martin Corp. Hampton, VA, United States)
Barnard, Ansley (Washington Univ. Seattle, WA, United States)
Date Acquired
August 25, 2013
Publication Date
February 1, 2011
Subject Category
Structural Mechanics
Report/Patent Number
L-19983
NASA/TM-2011-217049
NF1676L-12092
Report Number: L-19983
Report Number: NASA/TM-2011-217049
Report Number: NF1676L-12092
Funding Number(s)
WBS: WBS 727950.04.05.23
Distribution Limits
Public
Copyright
Public Use Permitted.

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