Carbon fibre composite wing manufacture

Details Carbon fibre composite wing manufacture Carbon fibre composite wing manufacture

1991-11-07

1993-06-08

Eley, Timothy V.

Metal working

Method of mechanical manufacture

Assembling or joining

29448, 244133, B23P 1102

Patent

active

052167992

ABSTRACT:
A method of constructing a carbon fiber composite wing in which upper and lower skins are bonded to a pre-assembled rib 15 and spar 16 framework, thus obviating the need for metal fasteners and hence cutting down assembly time. In one embodiment a novel cleat 17 of cruciform cross-section replaces the four cleats conventionally used for bolting the ribs 15 and spars 16 together. Holes 22 drilled in either end of the cleats serve as jig location points during framework assembly and anti-peel fastener holes after the skins have been bonded.

REFERENCES:
patent: 1603051 (1926-10-01), Hall
patent: 3519228 (1970-07-01), Windecker
patent: 3857150 (1974-12-01), Faucheux
patent: 4014089 (1977-03-01), Sato et al.
patent: 4530147 (1985-07-01), Mattei et al.
R. M. Gill, Carbon Fibres in Composite Materials, Fibres and Composite Materials, 1972, pp. 6-11.
Composites in aircraft construction, Flight International, 23 May 1981, pp. 1551-1552.
Schier & Juergens, Design Impact of Composites on Fighter Aircraft Part I, 1983 AIAA pp. 44-49.
New Materials Fly Better and Cheaper, Mechanical Engineering, May 1982, pp. 20-24.

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