Experimental investigations into composite fuselage impact damage resistance and post-impact compression behaviorImpact damage resistance and residual strength of laminated composite transport aircraft fuselage structure was studied experimentally. Techniques to quantify impact damage discretely and non-discretely are described. Experimental techniques to three-dimensionally map matrix damage and determine the sublaminate structure are illustrated. Impact damage was also quantified non-discretely, using characteristics of flexural wave propagation. Strain distributions in compressively loaded impact damaged laminates were experimentally measured.
Document ID
19930031815
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dost, E. F. (NASA Langley Research Center Hampton, VA, United States)
Finn, S. R. (Boeing Commercial Airplane Group Seattle, WA, United States)
Stevens, J. J. (NASA Langley Research Center Hampton, VA, United States)
Lin, K. Y. (Washington Univ. Seattle, United States)
Fitch, C. E. (Zetec, Inc. Issaquah, WA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Publication Information
Publication: In: International SAMPE Symposium and Exhibition, 37th, Anaheim, CA, Mar. 9-12, 1992, Proceedings (A93-15726 04-23)
Publisher: Society for the Advancement of Material and Process Engineering