Many aerospace parts suitable for composite materials feature complex geometric features such as angles, tight corner radii and interfaces with inserts, core materials, or hollow sections. The present study, a combination of controlled manufacturing and scale-up to demonstrators, seeks to understand the effect of such geometric complexities on the consolidation phenomena of OOA prepregs, with the overall aim of developing reduction or elimination strategies.
Composite optical micrograph of a 45° angle four-layer laminate manufactured using OOA prepreg. The corner shows thickening and resin accumulation due to reduced compaction and ply bridging.
