Structure for aircraft, method of manufacturing structure for aircraft and method of making design information of structure for aircraft

Patent metadata

Field	Value
Publication number	US-9957063-B2
Application number	US-201615048671-A
Country	US
Kind code	B2
Filing date	Feb 19, 2016
Priority date	Feb 23, 2015
Publication date	May 1, 2018
Grant date	May 1, 2018

Abstract

According to one implementation, a structure for an aircraft includes a first structural member, a second structural member coupled to the first structural member, a fastener and a conductive object. The fastener couples the first structural member to the second structural member. The fastener is inserted into an insertion hole formed in a portion where the first structural member is overlapped with the second structural member. The fastener is in electrically non-contact with the first and second structural members in the insertion hole. The conductive object is embedded inside at least either one of the first and second structural members. The conductive object prevents a spark between the fastener and each of the first and second structural members by forming a current pathway that leads current, flowing inside the at least either one of the first and second structural members, to the other structural member.

First claim

What is claimed is:

1. A structure for an aircraft comprising:
a first structural member;
a second structural member coupled to the first structural member;
a fastener that couples the first structural member to the second structural member, the fastener being inserted into an insertion hole formed in a portion where the first structural member is overlapped with the second structural member, the fastener being in electrically non-contact with each of the first structural member and the second structural member in the insertion hole; and
a conductive object of which at least a part is embedded inside at least either one of the first structural member and the second structural member, the conductive object preventing a spark between the fastener and each of the first structural member and the second structural member by forming a current pathway that leads current, flowing inside the at least either one of the first structural member and the second structural member inside which the at least the part is embedded, to the other structural member,
wherein a conductive layer is disposed between the first structural member and the second structural member, the conductive layer contacting with the conductive object.

2. The structure for the aircraft according to claim 1 ,
wherein the conductive object is disposed in the portion where the first structural member is overlapped with the second structural member.

3. The structure for the aircraft according to claim 1 ,
wherein the at least either one of the first structural member and the second structural member, inside which the at least the part of the conductive object is embedded, is made of a composite material.

4. The structure for the aircraft according to claim 1 ,
wherein the first structural member is a panel of a wing that serves as a casing of a fuel tank and the second structural member is an access panel to the fuel tank.

5. The structure for the aircraft according to claim 4 ,
wherein a bolt is disposed, as the conductive object, in the portion where the first structural member is overlapped with the second structural member, the bolt penetrating the first structural member from a side of the second structural member toward a fuel side, the second structural member being overlapped with an air side of the first structural member, and
wherein the structure for the aircraft further comprises:
a nut that fixes the bolt to the first structural member, the nut being fastened with a male screw formed on a tip portion of the bolt protruding from the first structural member to the fuel side; and
a protecting member that insulates the tip portion of the bolt and the nut.

6. The structure for the aircraft according to claim 1 ,
wherein a pin or a bolt is disposed as the conductive object, the pin or the bolt being inserted into a blind hole formed in the at least either one of the first structural member and the second structural member, an inlet of the blind hole being formed in a side where the first structural member is overlapped with the second structural member.

7. The structure for the aircraft according to claim 6 ,
wherein each of a first pin or a first bolt and a second pin or a second bolt is disposed as the conductive object, the first pin or the first bolt being inserted into a first blind hole formed in the first structural member, the second pin or the second bolt being inserted into a second blind hole formed in the second structural member, each of inlets of the first and second blind holes being formed in the side where the first structural member is overlapped with the second structural member, the first pin or the first bolt being electrically coupled with the second pin or the second bolt directly or indirectly.

8. The structure for the aircraft according to claim 1 ,
wherein the fastener is applied with an insulating sealant.

9. The structure for the aircraft according to claim 1 , further comprising:
a conductive shim disposed in a gap between the conductive object and the conductive layer, the shim forming a current pathway between the conductive object and the conductive layer.

10. A method of manufacturing a structure for an aircraft comprising:
manufacturing a first structural member;
manufacturing a second structural member to be coupled to the first structural member;
embedding at least a part of a conductive object inside at least either one of the first structural member and the second structural member, the conductive object forming a current pathway that leads current, flowing inside the at least either one of the first structural member and the second structural member, to the other structural member, the conductive object preventing a spark between a fastener and each of the first structural member and the second structural member, the fastener coupling the first structural member to the second structural member;
overlapping the first structural member with the second structural member, and forming an insertion hole in a portion where the first structural member is overlapped with the second structural member;
coupling the first structural member with the second structural member by inserting the fastener into the insertion hole, the fastener being in electrically non-contact with each of the first structural member and the second structural member in the insertion hole; and
disposing a conductive layer between the first structural member and the second structural member, the conductive layer contacting with the conductive object.

11. A method of making design information of a structure for an aircraft comprising:
designing a shape of a first structural member;
designing a shape of a second structural member to be coupled to the first structural member;
determining a position of a fastener that couples the first structural member with the second structural member, the fastener being inserted into an insertion hole formed in a portion where the first structural member is overlapped with the second structural member, the fastener being in electrically non-contact with each of the first structural member and the second structural member in the insertion hole;
determining a position of a conductive object of which at least a part is embedded inside at least either one of the first structural member and the second structural member, the conductive object preventing a spark between the fastener and each of the first structural member and the second structural member by forming a current pathway that leads current, flowing inside the at least either one of the first structural member and the second structural member inside which the at least the part of the conductive object is embedded, to the other structural member; and
determining to dispose a conductive layer between the first structural member and the second structural member, the conductive layer contacting with the conductive object.

12. A structure for an aircraft comprising:
a first structural member exposed to an atmosphere side;
a second structural member coupled to the first structural member;
a fastener that couples the first structural member to the second structural member, the fastener being inserted into an insertion hole formed in a portion where the first structural member is overlapped with the second structural member, the fastener being in electrically non-contact with each of the first structural member and the second structural member in the insertion hole; and
a conductive object of which at least a part is embedded inside at least either one of the first structural member and the second structural member, the conductive object preventing a spark between the fastener and each of the first st

Assignees

• Subaru Corp

Inventors

• Kawashima Ai
• Akiba Kousaburou
• Komaba Yasueki
• Hiromatsu Yoshiaki
• Nishi Takayuki
• Fujita Hiroyasu

Classifications

• B64D37/32

  Safety measures not otherwise provided for, e.g. preventing explosive conditions · CPC title

• B64C3/26

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

• B64D45/02 Primary

  Lightning protectors; Static dischargers · CPC title

• B64C3/34

  Tanks constructed integrally with wings, e.g. for fuel or water · CPC title

• B64C1/12

  Construction or attachment of skin panels · CPC title