Failure analysis of composite cylinders subject to internal blast
The response of advanced composite and 6061-T6 monocoque cylinders of the same length, radius and weight to a point internal blast detonation at the geometric center was computer analyzed. Composite skins were composed of uniaxial plies stacked in the axial, diagonal and hoop directions. The ratio o...
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Veröffentlicht in: | Engineering fracture mechanics 1976, Vol.8 (4), p.758-759 |
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Hauptverfasser: | , |
Format: | Artikel |
Sprache: | eng |
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Zusammenfassung: | The response of advanced composite and 6061-T6 monocoque cylinders of the same length, radius and weight to a point internal blast detonation at the geometric center was computer analyzed. Composite skins were composed of uniaxial plies stacked in the axial, diagonal and hoop directions. The ratio of critical-charge mass to fail high-strength graphite/epoxy (25 plies each in the 0, 45, -45, 90 degree directions) to that to fail a 6061-T6 cylinder was 0.33, or for 15, 15, 15, 55 plies, 0.41. Respective ratios of bending stiffness (composite/6061-T6) were 1.4; unity. Further increase of hoop plies would have reduced the bending stiffness below that of the 6061-T6. For B/epoxy and 11, 11, 11, 67 respective plies the critical-charge mass ratio was 0.36 and the bending stiffness ratio unity. Design recommendations for blast- tolerant composite helicopter tailcones and plans for more detailed analytic and experimental study were discussed.-- EPAA /AF. |
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ISSN: | 0013-7944 1873-7315 |
DOI: | 10.1016/0013-7944(76)90063-1 |