Wing and wing design method

Patent metadata

Field	Value
Publication number	US-11364989-B2
Application number	US-201816753172-A
Country	US
Kind code	B2
Filing date	Sep 10, 2018
Priority date	Oct 10, 2017
Publication date	Jun 21, 2022
Grant date	Jun 21, 2022

Abstract

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.

First claim

The invention claimed is:

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.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Nomura Takayuki
• Kodama Satoshi
• Yumitori Takaaki
• Takagi Kiyoka
• Shitani Tooru
• Abe Toshio

Classifications

• B64C3/20

  Integral or sandwich constructions · CPC title

• B64C3/26 Primary

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• B64C3/18 Primary

  Spars; Ribs; Stringers · CPC title