| 摘要 |
Fibre laminate (22) is produced by guiding rovings (10), formed of resin impregnated filaments and a predetermined distance apart, onto a surface (18) where they are compacted such that adjacent rovings are bonded together and a surface contoured band (22) is formed, pref. the inter-roving spacing being used to vary band height and filament density. Pref. each roving is firstly routed through a pair of tines of a fixed position comb and then between the tines of a comb or combs designed to alter the inter-roving spacing, these devices being a rotatable comb, an expandable and contractable comb having two sets of offset tines each receiving and guiding a different group of rovings, and a hinged comb pair having an adjustable hinge angle. Fibre laiminates can be produced quickly of any desired structure size, or shape. Method is partic. suitable for the mnf. of aircraft structural components such as tapered and contoured plies for wing skins meeting load requirements without using excess material. Method gives far superior results to those obtained using tape lay-up, cloth lay-up, and filament winding. |
