Wing and wing design method
A wing used for an aircraft includes a configuration member formed of a composite material. The configuration member is divided into a plurality of regions along a surface thereof. The plurality of regions include a first region formed of the composite material of a high strength type, and a second region formed of the composite material of a high elasticity type having higher rigidity than the high strength type. The first region includes any region closest to a wing end side out of the plurality of regions, and the second region includes a region closest to the wing end side and a trailing edge side out of the plurality of regions.
1. A wing used for an aircraft, comprising:
a configuration member formed of composite materials including a first composite material and a second composite material,
wherein the configuration member is divided into a plurality of regions along an upper surface of the wing,
wherein the plurality of regions include a first region formed of the first composite material, and a second region formed of the second composite material having rigidity higher than a rigidity of the first composite material of the first region, and
wherein the first region includes a region closest to both a wing end side and a leading edge side of the wing, and the second region includes a region closest to both the wing end side and a trailing edge side of the wing.
2. The wing according to claim 1 , wherein the plurality of regions are divided in a wing length direction and a wing chord direction orthogonal to the wing length direction.
3. The wing according to claim 2 , wherein the plurality of regions are divided in a grid shape in the wing length direction and the wing chord direction.
4. The wing according to claim 1 , wherein the plurality of regions are divided to have equal areas.
5. The wing according to claim 1 , wherein the configuration member is a skin.
6. A design method of an aircraft wing including a configuration member formed of composite materials including a first composite material and a second composite material, the method comprising:
dividing a surface of the configuration member into a plurality of regions along an upper surface of the aircraft wing;
setting each pattern of a first region and a second region by dividing the plurality of regions into the first region formed of the first composite material and the second region formed of the second composite material having a rigidity higher than a rigidity of the first composite material of the first region, the first region including a region closest to both a wing end side and a leading edge side of the wing, and the second region includes a region closest to both the wing end side and a trailing edge side of the wing;
calculating a flutter speed at which a flutter occurs in the wing, for each pattern by using a numerical analysis; and
determining the pattern that maximizes the calculated flutter speed, as an optimal pattern.