Design and analysis of multirow highly loaded bolt joints in composite wing structures

Developing effective methods for the design, analysis, and evaluation of multirow highly loaded bolt joints is an important element in the successful implementation of composite structures. This study describes method of analysis for the multirow highly loaded bolt joints in composite wing structures and several different designed test specimens are to verify the analysis and validate the analysis methodology. These designed specimens were made from S/RFI (Stitched/Resin Film-Infused) carbon fiber composite material and their load intensities were on the order of 50 to 60 kips per inch of specimen width for 0.94 inch thick pad-up skin.; The NASTRAN linear static and nonlinear analyses were used for both compression and tension high-load specimens with detail finite element models. PATRAN was used as pre- and post-processor to display the stress strain contour plots, deflections, and reaction freebody load for all the components.; Within this study several different fastener flexibility methods are compared and calculations for the single-shear, double-shear, and multiple splice/doubler joints with variation of types and sizes of fasteners. In the design and analysis of multirow highly loaded bolt joints in composite wing structures, uniform bolt loading is crucial to the joint design and, vigorous flexibility calculations as shown in this study should be considered.