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

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.

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.

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 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 the at least the part of the conductive object is embedded inside the at least either one of the first structural member and the second structural member to prevent the conductive object from being exposed to the atmosphere side.

A method of manufacturing a structure for an aircraft comprising:

• manufacturing a first structural member exposed to an atmosphere side;
• 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;
• and
• 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,
• wherein the at least the part of the conductive object is embedded inside the at least either one of the first structural member and the second structural member to prevent the conductive object from being exposed to the atmosphere side.

A method of making design information of a structure for an aircraft comprising:

• designing a shape of a first structural member exposed to an atmosphere side;
• 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;
• and
• 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,
• wherein the position of the conductive object is determined to prevent the conductive object from being exposed to the atmosphere side.