Patent ID: 6116539
Filing Date: 2000-09-12
Classification: B64C,Y02T

Abstract:
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.