Fatigue Behavior of Stitched Stiffened Composite Panel with Impact Damage

摘要

Textile structural composites with through-the-thickness reinforcement are promising materials for aircraft structural applications. In this work, compressive fatigue behavior of stitched, stiffened panels with clearly visible impact damage (CVFD) on the flange has been studied experimentally. The panels, having two blade stiffeners, are composed of 3501-6 epoxy resin and AS4-3k plain-weave fabrics stitched with Kevlar 2790 yarn. The panels were impacted at the flange area before fatigue tests. These impacted panels were tested in constant amplitude compression fatigue loading and modified transport wing standard test (TWIST) spectrum fatigue loading.