GB778681A - Improvements in or relating to aerofoils - Google Patents

Abstract

778,681. Aircraft framework. BRISTOL AIRCRAFT, Ltd. April 13, 1953 [April 15, 1952], No. 9477/52. Class 4. [Also in Group XXI] A wing assembly for an aircraft comprises two synthetic resin mouldings, each comprising an upper skin 20 with integrally moulded spanwise webs 27 and chordwise ribs 23-26 and a lower skin 21 similarly reinforced, the reinforcements and the leading and trailing edges of the wings being faced off at 22 on a common plane, the mating faces being adhesively secured together and reinforced by members 50. The wing portions are connected together by the ribs 23 which are adhesively secured together and reinforced by a strap plate inserted in a recess in the adjoining skin panels. An aileron 30 of similar construction is mounted on each wing portion, the ailerons being interconnected and operated by a mechanism 39-41. Attachment lugs 48 are attached to plates moulded into the ribs 24 whereby the wing may be secured to a fuselage of the type described in Specification 778,682. A variable incidence wing formed with a root spigot is also described for use with the above-mentioned fuselage. A tail unit is shown in Fig. 9 comprising aerofoil surfaces constructed as previously described wherein a tail end fuselage portion 77 carries a fin 70 which supports a tailplane 49 at its upper edge and a propulsion unit 94 at its lower edge. The elevators 65 are operated by control gear 100-103 and control gear 104 for a dive-brake umbrella is fitted. Specification 778,684 [Group VIII] also is referred to.