Review of the design process of a representative test specimen of a structural joint of a carbon‐epoxy aircraft

Abstract

The design process of a Representative Test Specimen (RTS) intended to reproduce the same state of stress of a complex‐in‐shape structural joint but with a simpler geometry is here inspected. The RTS corresponds to the joint of the fuselage with the main landing gear and the lower segment of the supporting strut of a strut‐braced, high wing aircraft fabricated with carbon‐epoxy composite. The design process of the RTS is based on the Multi‐Instrumented Technological Evaluators method, developed to reduce testing times and costs with respect to the standard Testing Pyramid approach. Complementary design methods comprise the Quality Functions Deployment articulated with the Functional Analysis. Afterward, once that the parametric design of the RTS is conducted with an iterative numerical analysis based on the Finite Element Method the outcome is a sandwich‐type structure to be tested with a non‐standardized three‐point bending test. In closing, the said design methods plus the numerical analysis foster an integral‐design approach in the outline of composite structures. POLYM. COMPOS., 40:E898–E911, 2019. © 2018 Society of Plastics Engineers