Several 1/16th-scale curved sandwich composite panel sections of a 10 m diameter barrel werefabricated to demonstrate the manufacturability of large-scale curved sections using minimumgauge, [+60/-60/0]S, toughened epoxy composite facesheets co-cured with low density (50kg/m3) aluminum honeycomb core. One of these panels was fabricated out of autoclave (OoA)by the vacuum bag oven (VBO) process using Cycom? T40-800b/5320-1 prepreg system whileanother panel with the same lay-up and dimensions was fabricated using the autoclave-cure,toughened epoxy prepreg system Cycom? IM7/977-3. The resulting 2.44 m × 2 m curved panelswere investigated by non-destructive evaluation (NDE) at NASA Langley Research Center(NASA LaRC) to determine initial fabrication quality and then cut into smaller coupons forelevated temperature wet (ETW) mechanical property characterization. Mechanical propertycharacterization of the sandwich coupons was conducted including edge-wise compression(EWC), and compression-after-impact (CAI) at conditions ranging from 25°C/dry to 150°C/wet.The details and results of this characterization effort are presented in this paper.
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