Design, testing, and damage tolerance study of bonded stiffened composite wing cover panels

Madan, Ram C.; Sutton, Jason O.

doi:10.2514/6.1988-2292

Cited by 4 publications

(2 citation statements)

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“…The design philosophy used was that impact energies greater than this level would be detected and repaired but damage that was "barely visible" might not be detected and therefore the wing would be required to carry DUL in the presence of this damage. Testing conducted during the early stages of the ACT program determined this energy level to be 135.5 J (100 ft-lb) [16].…”

Section: Impact Damage and Test Proceduresmentioning

confidence: 99%

Improving strength of postbuckled panels through stitching

Jegley

2007

Composite Structures

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The behavior of blade-stiffened graphite-epoxy panels with impact damage is examined to determine the effect of adding through-the-thickness stitches in the stiffener flange-to-skin interface. The influence of stitches is evaluated by examining buckling and failure for panels with failure loads up to 3.5 times greater than buckling loads. Analytical and experimental results from four configurations of panel specimens are presented. For each configuration, two panels were manufactured with skin and flanges held together with through-the-thickness stitches introduced prior to resin infusion and curing and one panel was manufactured with no stitches holding the flange to the skin. No mechanical fasteners were used for the assembly of any of these panels. Panels with and without low-speed impact damage were loaded to failure in compression. Buckling and failure modes are discussed. Stitching had little effect on buckling loads but increased the failure loads of impact-damaged panels by up to 30%.

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Section: Impact Damage and Test Proceduresmentioning

confidence: 99%

Improving strength of postbuckled panels through stitching

Jegley

2007

Composite Structures

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“…Many researchers have studied the behaviour of stiffened panel constructions and skinstiffener interfaces both theoretically and experimentally. A number of contributions in literature have addressed buckling, post-buckling and failure behaviour of stiffeners and stiffened panels using experimental and analytical approaches [2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19]. These papers have brought out clearly that the mode of damage onset is by the debonding of the stiffeners from the skin.…”

Section: Introductionmentioning

confidence: 99%