An experimental study of the compression response of fluted-core composite panels with joints

Abstract

Fluted-core sandwich composites consist of integral angled web members spaced between laminate face sheets, and may have the potential to provide benefits over traditional sandwich composites for certain aerospace applications. However, fabrication of large autoclave-cured fluted-core cylindrical shells with existing autoclaves will require that the shells be fabricated in segments, and joined longitudinally to form a complete barrel. Two different longitudinal fluted-core joint designs were considered experimentally in this study. In particular, jointed fluted-core-composite panels were tested in longitudinal compression because longitudinal compression is the primary loading condition in dry launch-vehicle barrel sections. One of the joint designs performed well in comparison with unjointed test articles, and the other joint design failed at loads approximately 14% lower than unjointed test articles. The compression-after-impact (CAI) performance of jointed fluted-core composites was also investigated by testing test articles that had been subjected to 6 ft-lb impacts. It was found that such impacts reduced the load-carrying capability by 9% to 40%. This reduction is dependent on the joint concept, component flute size, and facesheet thickness.

Novel filler materials for composite out-of-plane joints

“…Wang and Soutis [17] reported a 44% increase in ultimate tensile strength of a Tjoint interleaved with polyester (PE) veils compared to a pristine one, but this method is also limited to resin infusion. A cost-effective manufacturing process is pultrusion, but this requires the in-situ curing of the whole stiffener section and therefore it cannot be used for manufacturing individual fillers for later assembly in a prepreg structure [18].…”