Effect of Preforming Adherends on Static and Fatigue Strength of Bonded Composite Single-lap Joints
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1984 - Joints (Engineering) - 18 pages
An analytical and experimental investigation was conducted on bonded composite single-lap joints with the adherends preformed to reduce the angle between the line of action of the applied in-plane force and the bondline. A classical closed-form solution was used to analyze the composite joints with various preform angles and overlap lengths. The adherends of the test specimens were preformed before bonding, during the layup and curing process. Static tests were conducted for preform angles of 0 deg, 5 deg, 10 deg, and 15 deg and overlap lengths of 0.75, 1.75, 2.75, and 3.75 in. A limited fatigue study was conducted for specimens with a 2.75-in. overlap and a preform angle of 5 deg. Results of the analysis showed that preforming the adherends of bonded composite single-lap joints significantly reduced the shear and peel stress concentrations in the adhesive. Experimental results showed that preforming the adherends significantly increased their static and fatigue strength and thus increased the load level for which bonded composite single-lap joints can be designed. (MM).
3 pages matching baseline joint in this book
Results 1-3 of 3
What people are saying - Write a review
We haven't found any reviews in the usual places.
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