NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Impact damage resistance of composite fuselage structure, part 1The impact damage resistance of laminated composite transport aircraft fuselage structures was studied experimentally. A statistically based designed experiment was used to examine numerous material, laminate, structural, and extrinsic (e.g., impactor type) variables. The relative importance and quantitative measure of the effect of each variable and variable interactions on responses including impactor dynamic response, visibility, and internal damage state were determined. The study utilized 32 three-stiffener panels, each with a unique combination of material type, material forms, and structural geometry. Two manufacturing techniques, tow placement and tape lamination, were used to build panels representative of potential fuselage crown, keel, and lower side-panel designs. Various combinations of impactor variables representing various foreign-object-impact threats to the aircraft were examined. Impacts performed at different structural locations within each panel (e.g., skin midbay, stiffener attaching flange, etc.) were considered separate parallel experiments. The relationship between input variables, measured damage states, and structural response to this damage are presented including recommendations for materials and impact test methods for fuselage structure.
Document ID
19950022061
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dost, E. F. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Avery, W. B. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Ilcewicz, L. B. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Grande, D. H. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Coxon, B. R. (Integrated Technologies, Inc. Bothell, WA., United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1992
Publication Information
Publication: FAA, Ninth DOD(NASA)FAA Conference on Fibrous Composites in Structural Design, Volume 2
Subject Category
Aircraft Design, Testing And Performance
Accession Number
95N28482
Funding Number(s)
CONTRACT_GRANT: NAS1-18889
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

IDRelationTitle19950021999Collected WorksNinth DOD/NASA/FAA Conference on Fibrous Composites in Structural Design, volume 1
No Preview Available