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2.75-in-overlap specimens adherends of bonded adherends preformed adherends resulted aluminum bonded single-lap analytical and experimental analytical results applied in-plane force Average failure load baseline and preformed-adherend baseline joint bonded composite single-lap bonded joints bonded single-lap joints composite materials composite single-lap joints conducted for preform conducted for specimens Effect of preform fatigue strength fatigue tests Fiberglass end tabs increased overlap length increased the static joint failure joints significantly reduced joints with preformed Langley Research Center lap joint layup and curing lengths of 0.75 limited fatigue study longer overlaps maximum failure load NASA obtained by preforming optimum preform angle peel and shear peel stress concentrations preformed adherends preformed before bonding preformed to reduce preformed-adherend composite joints preformed-adherend specimens preforming the adherends shear and peel shear stress concentrations showed that preforming shown in figure single-lap joints significantly specimens were preformed static and fatigue static joint strength strength of bonded tests were conducted various preform angles