Experimental and semianalytical investigation of X850 ± IM190 CFRP bolted joints

Abstract

Considering the fact that the foundation data for a new X850 ± IM190 carbon/epoxy material system adopted in commercial aircraft industry are extremely scarce in the literature, an in-plane, static tensile experiment was carried out to investigate the bearing performance of double-lap, single-bolt joints in X850 ± IM190 carbon fiber-reinforced polymer (CFRP) composites. The effects of ply ratio, 0° layers’ combination percentage, bolt diameter, and curing method were considered. Then, special attention was paid to determine the design parameters of X850 ± IM190 CFRP bolted joints, such as tensile strength of un-notched laminate and stress concentration relief factor. Based on these design parameters, an efficient semianalytical approach was established to obtain the ultimate bearing strength of the joints. The failure prediction exhibited excellent agreement with the experimental data. These results will play an important role in design and strength evaluation of X850 ± IM190 CFRP bolted joints.

Numerical and experimental investigation on the load‐bearing performance of plain‐woven composites hybrid bonded‐bolted joints

“…[1][2][3][4] However, most of the plain-woven fabrics are manufactured as simple structures due to the complexity of the manufacturing process and the limitations of the current technology, such that the jointing methods should be adopted to connect the above plain-woven fabrics (e.g., plain-woven CFRP laminates) into desired structures with complete load transmission performance to satisfy the engineering requirements. [5][6][7] Therefore, the composites' jointing problem is inevitable. [8][9][10] Recently, the CFRP hybrid bondedbolted (HBB) joints have harvested a significant amount of attention for gathering advantages of adhesively bonded and mechanical bolted joints [11][12][13] and have been extensively employed in composite structures.…”

“…Plain‐woven carbon fiber‐reinforced plastic (CFRP) has been increasingly employed in advanced industrial fields (e.g., aerospace, marine, and automotive) for its excellent mechanical properties due to the interweaving of 0° and 90° fiber bundles in the respective ply 1–4 . However, most of the plain‐woven fabrics are manufactured as simple structures due to the complexity of the manufacturing process and the limitations of the current technology, such that the jointing methods should be adopted to connect the above plain‐woven fabrics (e.g., plain‐woven CFRP laminates) into desired structures with complete load transmission performance to satisfy the engineering requirements 5–7 . Therefore, the composites' jointing problem is inevitable 8–10 .…”