GB876438A - Improvements in and relating to the wings of aircraft - Google Patents

Abstract

876,438. Aircraft framework. BLACKBURN AIRCRAFT Ltd., PROWER, C. W., and HAND, P. G. E. Jan. 29, 1960, No. 3308/60. Class 4. A joint connects the centre section of a tapered thickness wing or wing portion 1 to the corresponding section of another wing of tapered thickness 2 or to a wing portion of constant thickness, in which the sparbooms 3 and stringers 4 terminate between and are bolted to pairs of attachment plates 10, 11 matching the crosssectional shape of the wing and bent beyond the ends of the sparbooms 3 and stringers 4 to form portions of uniform . spacing which are bolted with the interpositioning of a spacer 13 between each pair of plates 10, 11 to flanges 7, 8 on one side of a vertical beam 6 matching the cross-sectional shape of the wing and situated in a portion of constant thickness between two wings or at the end of the constant thickness portion of the wing. As shown, the wing sections each comprise spar-booms 3, stringers 4 and skin plating 5. At the junction of the wings 1, 2 is a vertical beam 6 with stiffening ribs 9, at the top and bottom of which are parallel flanges 7, 8. The ends of the sparbooms 3 and stringers 4 are disposed between and secured to, by a row of bolts 12, two plates 10, 11, which are so bent that the portions extending beyond the ends of the members 3 and 4 are in the planes of the flanges 7, 8. Together with an intermediate spacer 13 and junction plate 16, the overlapping parts of the plates 10, 11 are secured by bolts 14, 15 to the flanges 7, 8. The junction plates 16 have separate end sections 20, which are secured by U-bolts 21 to the members 18, themselves secured to the spar-booms 3 by bolts 19.