GB392905A - Improvements in fuselage bodies for aircraft - Google Patents

Abstract

392,905. Aircraft fuselages. VICKERS (AVIATION), Ltd. and WALLIS, B. N., Weybridge Works, Byfleet Road, Weybridge, Surrey. Nov. 23, 1931, No. 32397. [Class 4.] An aircraft fuselage of the stressed skin type comprises a series of spaced polygonal transverse frames 5, Fig. 2, interconnected at the corners by longitudinal members 10 and a skin comprising a number of sheets of thin material arranged in a series of flat panels bounded by adjacent longitudinal members to which they are secured at their overlapping borders. In one form, Fig. 4, the frames 5 are of open lattice work comprising inner and outer members 6, 7, united by radial members 8 and crossed diagonals 9. According to various modifications, the members 8 may be omitted or the inner member 6 may be assymetrical, for instance of diamond shape and be connected to member 7 by Warren girder cross bracing. Transverse frames according to any of these modifications may be used in combination in one fuselage. The longitudinal members 10 are of angle section and are secured by gussets 11 riveted at the points 12 to frame 5. The gussets are cut away at 13 to permit passage of the longitudinal and formed with upstanding flanges 14 which are riveted at 15 to downwardly extending arms of the longitudinals 10. The skin is constituted by strips of thin sheet metal 17 arranged with their borders 18 overlapping, the overlapping borders being secured to members 10 by a line of rivets 16. Borders 18 of each strip are shown bent to the shape of frames 5 but according to a modification only one border of each strip may be bent. Diagonal members such as 19, Fig. 2, may be employed to reinforce the forward fuselage panel.