Blade member for airplane
View Patent ↗It is an object to provide a blade member for an airplane which is simple in structure, and moreover is excellent with respects to weight, aerodynamic performance, cost, strength and durability. A vane of a double-slotted flap includes: an outer skin area surrounded by a first outer skin, a second outer skin, a leading edge and a trailing edge each having a predetermined wall thickness. Front and rear reinforcing areas are provided that extend in a span direction within the outer skin area and are connected to the first outer skin and the second outer skin. The outer skin area and the reinforcing areas are integrally formed by wire electrical discharge-machining. The first outer skin and the second outer skin respectively have thickened portions thicker than the other portions, and the trailing edge is formed to have a thickness which is approximately zero. This blade member can be simplified in structure, leading to reductions in the number of parts, number of assembling steps and weight. Moreover, no step nor seam is generated on a surface of the blade member, and hence it is possible to prevent an increase in drag and the generation of corrosion.
1. A blade member for an airplane, which constitutes at least a portion of a rotor blade of the airplane, said blade member comprising:
an outer skin area surrounded by a first outer skin, a second outer skin, a leading edge and a trailing edge each having a predetermined wall thickness; and
at least one reinforcing area extending in a span direction within the outer skin area and connected to the first outer skin and the second outer skin,
wherein said outer skin area including said first outer skin, said second outer skin, said leading edge and said trailing edge and said reinforcing area are integrally formed from a single block by wire electrical discharge-machining, and
wherein the wall thickness of the first outer skin includes a central portion that is thicker relative to a portion adjacent to the leading edge and a portion adjacent to the trailing edge,
wherein two reinforcing areas are provided within the outer skin area for connecting the first outer skin to the second outer skin,
wherein the at least one of wall thicknesses of said first outer skin and said second outer skin changes in a cord direction between a first of said two reinforcing areas and a second of said two reinforcing areas, with a portion the wall thickness of said first outer skin adjacent to the first of said two reinforcing area being thicker than a portion the wall thickness of said first outer skin adjacent to the second of the two reinforcing area.
2. The blade member for an airplane according to claim 1 , wherein a distance between outer surfaces of said first outer skin and said second outer skin is gradually decreasing toward the trailing edge to become approximately zero at the trailing edge.
3. The blade member for an airplane according to claim 1 , wherein the blade member is constructed of an aluminum alloy.
4. The blade member for an airplane according to claim 1 , wherein the first outer skin is curved upwardly.
5. The blade member for an airplane according to claim 1 , wherein said second outer skin is substantially flat.
6. A blade member for an airplane, which constitutes at least a portion of a rotor blade of the airplane and has an asymmetrical cross-sectional shape as viewed in a span direction, said blade member comprising:
an outer skin area elongated in the span direction and surrounded by a first outer skin, a second outer skin, a leading edge and a trailing edge each having a predetermined wall thickness; and
at least one reinforcing area extending in the span direction within the outer skin area and connected to the first outer skin and the second outer skin,
wherein the first outer skin and the second outer skin each have a thick wall portion and a thin wall portion, wherein the thick wall portions of the first and second outer skins are offset relative to each other in a cord direction, and wherein said outer skin area including said first outer skin, said second outer skin, said leading edge and said trailing edge and said reinforcing area are integrally formed from a single block by wire electrical discharge-machining.
7. The blade member for an airplane according to claim 6 , wherein the thick wall portion of the second outer skin is forward in the cord direction relative to the thick wall portion of the first outer skin.
8. The blade member for an airplane according to claim 6 , wherein said outer skin area including said first outer skin, said second outer skin, said leading edge and said trailing edge and said reinforcing area are integrally formed from a single block by wire electrical discharge-machining.