초록

A wing cover panel for an aircraft wing is formed as a plurality of sections each carrying stringer sections which are then fixed together to form a wing cover panel with an integral hollow stringer.

대표청구항 ▼

1. A method of forming a single skin wing cover panel for an aircraft wing, said method comprising the steps of: a) forming first and second single skin cover panel sections each comprising:a single skin panel member having a first edge, an aerofoil surface on one side, and a non aerofoil surface on

1. A method of forming a single skin wing cover panel for an aircraft wing, said method comprising the steps of: a) forming first and second single skin cover panel sections each comprising:a single skin panel member having a first edge, an aerofoil surface on one side, and a non aerofoil surface on the other side; anda first flange projecting away from said non aerofoil surface and having a projecting edge in a generally parallel plane relative to said first edge, wherein said first and said projecting edges are disposed in a same plane;b) tapering said first edge of said single skin panel member and said projecting edge of said first flange of at least one of said single skin cover panel sections in a spanwise direction; and,c) fixing said first single skin cover panel section to said second single skin cover panel section by joining said respective first edges of said first and said second single skin panel members and joining said projecting edges of said respective first flanges of said first and said second single skin cover panel sections so as to form a single skin wing cover panel having a single integral stringer having a closed and hollow cross-section tapered in the spanwise direction. 2. A method according to claim 1 in which said first flange and said respective single skin panel member are integrally formed. 3. A method according to claim 1 in which at least one of said single skin cover panel sections further comprises a second flange projecting away from said non aerofoil surface in a generally parallel plane relative to a second edge of said respective single skin panel member, said second edge being generally opposite said first edge. 4. A method according to claim 1 in which said stringer has a box cross-section, each said first flange providing a part of said box cross-section. 5. A method according to claim 1 in which at least one of said single skin cover panel sections is formed having said projecting edge of said first flange and said first edge of said single skin panel member lying in a plane generally perpendicular to said respective aerofoil surface. 6. A method according to claim 1 in which at least one of said single skin cover panel sections is formed having said projecting edge of said first flange and said first edge of said single skin panel member lying in a radial plane relative to said respective aerofoil surface so that when said first and second single skin cover panel sections are fixed together, a combined aerofoil surface defined by said aerofoil surfaces of said single skin cover panel sections is concave. 7. A method according to claim 1 in which at least one of said single skin cover panel sections is formed having said projecting edge of said first flange and said first edge of said single skin panel member both lying in a radial plane relative to said respective aerofoil surface so that when said first and second single skin cover panel sections are fixed together, a combined aerofoil surface defined by said aerofoil surfaces of said single skin cover panel sections is convex. 8. A method according to claim 1 in which said single skin wing cover panel sections are extruded. 9. A method according to claim 1 in which said single skin wing cover panel sections are extruded and said tapering is provided by machining said at least one single skin wing cover panel section. 10. A method according to claim 1 in which said first and second single skin wing cover panel sections are fixed together by welding. 11. A method according to claim 1 in which said first and second single skin wing cover panel sections are formed from metal or metal alloy. 12. A single skin wing cover panel for an aircraft, said single skin wing cover panel comprising first and second single skin cover panel sections, each said single skin cover panel section comprising: a single skin panel member having a first edge, an aerofoil surface on one side, and a non aerofoil surface on the other side; anda first flange projecting away from said non aerofoil surface and having a projecting edge in a generally parallel plane relative to said first edge, wherein said first and said projecting edges are disposed in a same plane;whereinsaid first edge of said single skin panel member and said projecting edge of said first flange of at least one of said skin cover panel sections are tapered in a spanwise direction,said respective first edges of said first and said second single skin panel members are joined together, and said projecting edges of said respective first flanges of said first and said second single skin cover panel sections are joined together so as to form said single skin wing cover panel having a single integral stringer having a closed and hollow cross-section tapered in the spanwise direction. 13. A single skin wing cover panel according to claim 12 in which said first flange and said respective single skin panel member are integrally formed. 14. A single skin wing cover panel according claim 12 in which at least one of said single skin cover panel sections further comprises a second flange projecting away from said non aerofoil surface in a generally parallel plane relative to a second edge of said respective single skin panel member, said second edge being generally opposite said first edge. 15. A single skin wing cover panel according to claim 12 in which said stringer has a box cross-section, each said first flange providing a part of said box cross-section. 16. A single skin wing cover panel according to claim 12 in which at least one of said single skin cover panel sections is formed having said projecting edge of said first flange and said first edge of said single skin panel member lying in a plane generally perpendicular to said respective aerofoil surface. 17. A single skin wing cover panel according to claim 12 in which at least one of said single skin cover panel sections is formed having said projecting edge of said first flange and said first edge of said single skin panel member lying in a radial plane relative to said respective aerofoil surface so that when said first and second single skin cover panel sections are fixed together, a combined aerofoil surface defined by said aerofoil surfaces of said single skin cover panel sections is concave. 18. A single skin wing cover panel according to claim 12 in which at least one of said single skin cover panel sections is formed having said projecting edge of said first flange and said first edge of said single skin panel member both lying in a radial plane relative to said respective aerofoil surface so that when said first and second single skin cover panel sections are fixed together, a combined aerofoil surface defined by said aerofoil surfaces of said single skin cover panel sections is convex. 19. A single skin wing cover panel according to claim 12 in which said single skin wing cover panel sections are extruded. 20. A single skin wing cover panel according to claim 12 in which said single skin wing cover panel sections are extruded and said tapering is provided by machining said at least one single skin wing cover panel section. 21. A single skin wing cover panel according to claim 12 in which said first and second single skin wing cover panel sections are fixed together by welding. 22. A single skin wing cover panel according to claim 12 in which said first and second single skin wing cover panel sections are formed from metal or metal alloy. 23. A single skin cover panel section for assembly into a single skin wing cover panel for an aircraft, said single skin cover panel section comprising: a single skin panel member having a first edge, an aerofoil surface on one side, and a non aerofoil surface on the other side; anda first flange projecting away from said non aerofoil surface and having a projecting edge in a generally parallel plane relative to said first edge, wherein said first and said projecting edges are disposed in a same plane,whereinsaid first edge of said single skin panel member and said projecting edge of said first flange of at least one of said skin cover panel sections are tapered in a spanwise direction,said single skin cover panel section is arranged to be fixed to a correspondingly formed second single skin cover panel section by joining said first edge of said single skin panel member to a corresponding edge of said second single skin cover panel section and joining a projecting edge of said first flange to a corresponding edge of said second single skin cover panel section so as to form a single skin wing cover panel having a single integral stringer having a closed and hollow cross-section tapered in the spanwise direction.