초록 ▼

The instant invention generally relates to a forwardly swept wing 10 for an aircraft comprised of a pair of opposed single piece machined aluminum alloy wing boxes 20 and 40. Specifically, the invention provides for a forward swept wing construction utilizing known in the art computer numerical cont

The instant invention generally relates to a forwardly swept wing 10 for an aircraft comprised of a pair of opposed single piece machined aluminum alloy wing boxes 20 and 40. Specifically, the invention provides for a forward swept wing construction utilizing known in the art computer numerical control machining techniques to produce an aluminum alloy wing 10 having an integral leading edge 24 thereby greatly reducing assembly time. A plurality of integral stiffeners 80 oriented at a forwardly swept angle of approximately 12 to 13 degrees between forward 62 and rear 64 spars provides for a wing 10 that minimizes the effects of aeroelastic divergence.

대표청구항 ▼

[ What is claimed is:] [1.] A forward-swept wing for an aircraft having a fuselage comprising:an upper wing box machined from an aluminum alloy workpiece comprising;an upper wing skin defining an upper surface of an airfoil including a wing leading edge thereon, the leading edge having an upper port

[ What is claimed is:] [1.] A forward-swept wing for an aircraft having a fuselage comprising:an upper wing box machined from an aluminum alloy workpiece comprising;an upper wing skin defining an upper surface of an airfoil including a wing leading edge thereon, the leading edge having an upper portion and a lower rabbeted portion terminating at a point below the stagnation region of said wing;a forward spar proximate the leading edge of said wing extending laterally from wing root to wing tip, the forward spar further extending downwardly to the maximum thickness of said workpiece;a rear spar extending laterally from wing root to wing tip and arranged in generally parallel spaced relation to the forward spar;a plurality of stiffeners disposed between the forward spar and the rear spar at a forwardly swept angle of approximately 13 degrees to a laterally extending central axis of said wing to minimize aeroelastic divergence thereof;a plurality of ribs extending between the forward spar and the rear spar at an angle of approximately 90 degrees to the mean chord line of said wing; anda lower wing box machined from an aluminum alloy workpiece comprising;a lower wing skin defining a lower surface of an airfoil;a forward spar proximate the leading edge of said wing extending laterally from wing root to wing tip, said forward spar further extending upwardly to the maximum thickness of said workpiece;a rear spar extending laterally from wing root to wing tip and arranged in generally parallel spaced relation to the forward spar;a plurality of stiffeners disposed between the forward spar and the rear spar at a forwardly swept angle of approximately 13 degrees to a laterally extending central axis of said wing to minimize aeroelastic divergence thereof;a plurality of ribs disposed between the forward spar and the rear spar at an angle of approximately 90 degrees to the mean chord line of said wing; andan intermediate spar interposed between and welded to the forward spar of said lower wing box and the forward spar of said upper wing box for providing sufficient thickness to the leading edge of said wing.