GB480269A - An improved self supporting wing or control surface for aircraft - Google Patents

Abstract

480,269. Aircraft wing-structures. A.T.S. CO., Ltd., and NORTH, J. D. Aug. 20, 1936, No. 22938. [Class 4] A cantilever aeroplane wing or control surface includes main spars 1, 2 and a covering adapted to resist shearing forces, and the covering extends between the spars of an outer portion of the wing and forms together with the spars tubular members 18, 19 for the inner portion of the wing at which part, either or both the top and bottom covering between the spars are detachable ; the two wing parts are provided with strong rib members 9, 10 adapted to be connected so as to transmit the torsional and shear forces existing in the outer wing portion to the inner wing portion. As shown, the 'spars comprise T-booms and plate webs provided with stiffeners. The spars pass through the body and are continuous throughout the span of the inner wing portion. The outer wing portions comprise spars 7, 8, Z-sectioned stringers 11, 13 and ribs 12. The rib 14 is reinforced. The inner wing portions include a covering of greater thickness than that for the remainder of the wing, stringers and frames 21. The covering between the spars is stiffened by ribs 23 designed to accommodate, e.g. a fuel tank or retractable undercarriage. The wing covering is flanged and connected to the side plating of the body and the spar booms are connected to members 24. The inner sections of the wing are provided with flanged-plate stiffening members. The spar booms of the two portions of the wing are connected by interengaging members 6 connected by a pin or bolt. The members 6 are bolted to the rib web and to the spars, the rib flanges being reinforced by strips 27. The spar booms are recessed so that the rib flanges which pass over or under them do not project. The flanges and spars being connected by screws or rivets. The gap between the wing parts is covered by a strip 28.