Fatigue of Fibrous Composite MaterialsASTM International, 1981 |
Contents
Introduction | 1 |
Bolt Hole Growth in GraphiteEpoxy Laminates for Clearance | 21 |
Experimental and Analytical Study of Fatigue Damage in Notched | 48 |
Effect of Ply Constraint on Fatigue Damage Development | 64 |
Damage Initiation in a ThreeDimensional CarbonCarbon | 85 |
Mechanism of Fatigue In BoronAluminum Compositesm gouda | 101 |
Effects of Proof Test on the Strength and Fatigue Life of | 116 |
Fatigue Characterization of Composite Materialsj m Whitney | 133 |
Fatigue Behavior of GraphiteEpoxy Laminates at Elevated | 152 |
Compression Fatigue Behavior of GraphiteEpoxy in the Presence | 174 |
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Common terms and phrases
Air Force American Society amplitude analysis appears applied assumed ASTM axial bolt buckling calculated compared Composite Materials compression constant constraint crack cycles cyclic loading damage degradation delamination dependence determined direction distribution effect estimates experimental failed failure fatigue behavior fatigue failure fatigue loading fatigue tests fiber Figure flight fracture fracture surfaces function given graphite/epoxy growth higher hole impact increase indicate initiation laminate matrix maximum mean measured Mechanics method mode modulus notched noted observed obtained occur off-axis angle panel parameter percent plies plotted points predicted presented procedure proof load properties range ratio reduced REFERENCE residual strength respectively S-N curve sample sequence shear shown in Fig shows Society for Testing specimens spectrum static strength statistical strain stress level structures Table temperature tension Testing and Materials transverse Type values