Wing, flying object, and method for manufacturing a wing

Patent metadata

Field	Value
Publication number	US-11697489-B2
Application number	US-202117233743-A
Country	US
Kind code	B2
Filing date	Apr 19, 2021
Priority date	May 25, 2020
Publication date	Jul 11, 2023
Grant date	Jul 11, 2023

Abstract

A wing includes: a main structural member; a leading-edge member formed of material with a coefficient of linear thermal expansion different from that of material of the main structural member; an eccentric bushing that has a circular through-hole and is shaped in a cylindrical shape; and a coupling member. The leading-edge member has a first hole prolonged in a specific direction. The main structural member has a second hole. The center axis of the eccentric bushing and the center axis of the through-hole are parallel to and offset from each other. The eccentric bushing is inserted to the first hole. The first coupling member is inserted to the through-hole and the second hole to couple the main structural member and the leading-edge member.

First claim

What is claimed is:

1. A wing, comprising:
a main structural member;
a leading-edge member formed of material with a coefficient of linear thermal expansion different from that of material of the main structural member;
an eccentric bushing shaped in a cylindrical shape, wherein a circular through-hole is formed through the eccentric bushing; and
a first coupling member,
wherein the leading-edge member has a first hole elongated in a specific direction,
wherein the main structural member has a second hole,
wherein a center axis of the eccentric bushing and a center axis of the through-hole are parallel to and offset from each other,
wherein the eccentric bushing is inserted in the first hole, and
wherein the first coupling member is inserted in the through-hole and the second hole to couple the main structural member and the leading-edge member.

2. The wing according to claim 1 , wherein the main structural member comprises:
a first flange portion through which the second hole is formed; and
a second flange portion positioned opposed to the first flange portion, wherein a third hole is formed through the second flange portion,
wherein the leading-edge member comprises an insert through which the first hole is formed,
wherein the insert is inserted in a recess formed between the first flange portion and the second flange portion, and
wherein the first coupling member is inserted in the third hole.

3. The wing according to claim 1 , wherein the leading-edge member comprises:
a body having an opposing face opposed to the main structural member; and
a protrusion disposed to protrude from the opposing face of the body, wherein the first hole is formed through the protrusion, and
wherein the main structural member and the leading-edge member are coupled such that a gap is disposed between the main structural member and the leading-edge member.

4. The wing according to claim 1 , further comprising a second coupling member,
wherein the leading-edge member has a fourth hole with a circular shape at a position closer to a wing root of the wing than that of the first hole,
wherein the main structural member has a fifth hole with a circular shape at a position closer to the wing root than that of the second hole, and
wherein the second coupling member is inserted in the fourth hole and the fifth hole to couple the main structural member and the leading-edge member.

5. The wing according to claim 4 , further comprising a third coupling member,
wherein the leading-edge member has a sixth hole with a circular shape at a position between the first hole and the fourth hole,
wherein the main structural member has a seventh hole with a circular shape at a position between the second hole and the fifth hole, and
wherein the third coupling member is inserted in the sixth hole and the seventh hole to couple the main structural member and the leading-edge member.

6. The wing according to claim 1 , wherein the leading-edge member is formed of heat resistant material.

7. A flying object, comprising:
a fuselage; and
a wing, comprising:
a main structural member;
a leading-edge member formed of material with a coefficient of linear thermal expansion different from that of material of the main structural member;
an eccentric bushing shaped in a cylindrical shape, wherein a circular through-hole is formed through the eccentric bushing; and
a first coupling member,

wherein the leading-edge member has a first hole elongated in a specific direction,
wherein the main structural member has a second hole,
wherein a center axis of the eccentric bushing and a center axis of the through-hole are parallel to and offset from each other,
wherein the eccentric bushing is inserted in the first hole, and
wherein the first coupling member is inserted in the through-hole and the second hole to couple the main structural member and the leading-edge member.

8. The flying object according to claim 7 , wherein the main structural member comprises:
a first flange portion through which the second hole is formed; and
a second flange portion positioned opposed to the first flange portion, the second flange portion having a third hole,
wherein the leading-edge member comprises an insert through which the first hole is formed,
wherein the insert is inserted in a recess formed between the first flange portion and the second flange portion, and
wherein the first coupling member is inserted in the third hole.

9. The flying object according to claim 7 , wherein the leading-edge member is formed of heat resistant material.

10. A method of manufacturing a wing, comprising:
preparing a main structural member, a leading-edge member formed of material with a coefficient of linear thermal expansion different from that of material of the main structural member, and an eccentric bushing shaped in a cylindrical shape, wherein the eccentric bushing has a circular through-hole, and wherein the eccentric bushing has a center axis parallel to and offset from a center axis of the through-hole;
forming a first hole through the leading-edge member, the first hole being elongated in a specific direction;
forming a second hole through the main structural member;
inserting the eccentric bushing in the first hole; and
inserting a coupling member in the through hole and the second hole to couple the main structural member and the leading-edge member.

11. The method according to claim 10 , wherein the first hole and the second hole are formed in a state in which the main structural member and the leading-edge member do not overlap each other.

12. The method according to claim 10 , wherein the leading-edge member is formed of heat resistant material.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Kanazawa Yu
• Katsunaga Kenta
• Ogimura Koji

Classifications

• F42B10/06

  Tail fins · CPC title

• B64C3/28 Primary

  Leading or trailing edges attached to primary structures, e.g. forming fixed slots · CPC title