GB387904A - Improved framework for the wings of aeroplanes - Google Patents

Abstract

387,904. Aircraft wing structures. MESSIER, G. L. R. J., 29, Avenue Leon Gambetta, Montrouge, Seine, France. June 14, 1932, No. 16815. Convention date, Oct. 29, 1931. [Class 4.] A system of internal bracing for a single spar wing which is designed to prevent the transmission of torsion loads to the spar comprises a rearwardly extending member 5, Fig. 3, fixed to spar L and braced to the body by rigid intersecting members 10, 12 forming a cross having its corners attached to the body at the spar root 11 and at 13, to the spar at 14 and to member 5 at 7. The members 10, 12 may be of lozenge shape and serve to relieve the spar of torsional stresses such as would be produced by a force F<1> and also to relieve the spar of flexional stresses in the plane of the wing. More than one rearwardly extending arm may be employed as shown in Fig. 2 in which arms 5, 6 are braced together by members 10', 12<1> in the same way as arm 5 is braced to the body. The ribs of the wing rest at their rear ends on rigid or non-rigid members 9. Members 9 may be supported intermediate of the ends of the rearwardly extending members by lozenge-shaped parts such as 15 connected to the spar at their inner ends and centrally to the members 10<1>, 12<1>. The system of bracing described may be arranged in front of the spar or two systems one in front and one behind may be used. The spars may be interconnected in the manner described in Specification 375,733.