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ameyard, the fibres are carbon fibre in fabric and UD form. Could you be more specific with regards to the material permissible stresses and strains

Is composite wing mainly of quasi layup construction? and is it only for the only skins or the stiffeners like spars, ribs and stringers. I came across a presentation mentioning using unbalanced layup on the wing design to overcome the twisting, is this just simply add on extra plies on a quasi...

Thanks SWC, Question, don't the fibre strength and thickness of the laminate play any part in the pullout strength

Gents, Can pullout strength (e.g. of an insert or bolt)of composite be determined by analysis??

Thanks SWComposites for your info. I did find an article by Dr. DF Adams (High Performance Composites -March 2006)

Does anyone has any info on using Backout factors in calculating UD (0 degree) lamina property from crossply (0/90) laminate Thanks in advance

Is FyreRoc from Goodrich (goodr.com) anygood??

Try curing Hexcel 8552 epoxy (or any TGDDM-DDS epoxy system) at around 135c for 1 hour followed by 175C for 2 hours and finally postcure at 250C for 2.5 hours, you should get at Tg around 250C