초록 ▼

An airfoil for use in kites, movable wing aircraft and fixed wing aircraft has a straight spar inserted into a sleeve in the arcuate leading edge of a flexible wing panel. The resultant forces on the spar dynamically shape the airfoil. The airfoil is reinforced by battens between the leading edge an

An airfoil for use in kites, movable wing aircraft and fixed wing aircraft has a straight spar inserted into a sleeve in the arcuate leading edge of a flexible wing panel. The resultant forces on the spar dynamically shape the airfoil. The airfoil is reinforced by battens between the leading edge and the trailing edge of the wing panel. Flight control is maintained through control lines warping the airfoil.

대표청구항 ▼

I claim: 1. In an aerial vehicle capable of controlled flight, an airfoil comprising a flexible wing panel having a leading edge and a trailing edge separated by a chord with a wing tip at each end of said wing panel, said leading edge of said wing panel formed in an arc to increase said length of

I claim: 1. In an aerial vehicle capable of controlled flight, an airfoil comprising a flexible wing panel having a leading edge and a trailing edge separated by a chord with a wing tip at each end of said wing panel, said leading edge of said wing panel formed in an arc to increase said length of said chord between each said wing tip, a flexible spar attached to said leading edge whereby said spar is dynamically loaded to conform with said leading edge arc shaping camber to said airfoil wherein said wing panel includes a plurality of stiffeners attached to said wing panel and extending along said chord of said wing panel from said leading edge to said trailing edge and being spaced apart along the length of said wing panel between each said wing tip, said plurality of stiffeners being independent from said flexible spar. 2. In an aerial vehicle of claim 1 wherein said flexible wing panel is formed of a high strength fabric. 3. In an aerial vehicle of claim 1 wherein said flexible wing panel is formed of a high strength film. 4. In an aerial vehicle of claim 1 wherein an arcuate tube is attached to said leading edge of said flexible wing panel, said spar disposed within said tube and extending between each said wing tip. 5. In an aerial vehicle of claim 1 wherein separate control lines are attached to said spar, said separate control lines adapted to be manipulated by a pilot, movement of said separate control lines changing the shape of said wing panel and moving the center of gravity, respectively. 6. In an aerial vehicle of claim 1 wherein said airfoil is attached to an airframe intermediate each said wing tip whereby an equal length of said airfoil is located on opposite sides of said airframe. 7. In an aerial vehicle of claim 1 wherein a plurality of airfoils are attached to an airframe, each said airfoil movably connected to said airframe at one said wing tip whereby at least one airfoil extends on each opposite side of said airframe. 8. In an aerial vehicle of claim 7 wherein one of said plurality of airfoils attached to the airframe is a canard. 9. In an aerial vehicle of claim 1 wherein said arc has a known radius, said spar has a known straight length, said spar extending from one said wing tip to the other said wing tip, said length of said spar approximately 43% of said radius providing camber. 10. In an aerial vehicle of claim 1 wherein said wing panel a plurality of tunnels is formed in said wing panel, said plurality of stiffeners housed in said plurality of tunnels, respectively. 11. In a method of making an airfoil the steps comprising a) providing a first flat panel of flexible material; b) shaping said panel in a narrow elongated form having a leading edge and a trailing edge separated by a chord, said leading edge and said trailing edge intersecting at each end of said elongated form; c) forming said leading edge in an arc such that the intermediate chord is longer than each end; d) providing a flexible straight spar of a length to extend between said ends of said elongated form; e) bending said spar and attaching said spar to said arc of said leading edge; and f) forming camber in said flat panel resulting from the dynamic bending of said spar to conform to said arc including the step of attaching stiffeners solely to said panel extending along the length of said chord at spaced intervals independent of said spar. 12. In a method of making an airfoil of claim 11 including the steps of a) providing a second flat panel; b) shaping said second panel in a narrow elongated form having a leading edge and a trailing edge separated by a chord, said leading edge and said trailing edge intersecting at each end of said elongated form, c) joining said first panel and said second panel along said first and second leading edge whereby the periphery of said first panel and said second panel are approximately co-terminus whereby said first panel is the upper surface of said airfoil and said second panel is the lower surface of said airfoil resulting in camber and thickness of said airfoil. 13. In a method of making an airfoil of claim 11 including the steps of a) providing said leading edge with a separate hem along said leading edge; b) folding said hem upon itself to form a sleeve; c) attaching the free ends of folded sleeve to said panel; d) providing a straight spar; e) inserting said straight spar in said sleeve thereby deforming said spar to conform with said sleeve. 14. In a method of making an airfoil of claim 11 including the steps of a) providing a second flat panel; b) shaping said second panel in a narrow elongated form having a leading edge and a trailing edge separated by a chord, said leading edge and said trailing edge intersecting at each end of said elongated form, c) providing said first and second leading edge with a separate hem along said first and second leading edge; b) folding said hem upon itself to form a sleeve; c) attaching one of the free ends of folded sleeve to said first panel and the other of the free ends to said second panel such that the periphery of said first and said second panel is approximately co-terminus whereby said first panel is the upper surface of said airfoil and said second panel is the lower surface of said airfoil. 15. In a method of making an airfoil of claim 11 including the steps of forming a plurality of tunnels in said flat panel and inserting said plurality of stiffeners in said plurality of tunnels, respectively.