Method of joining structural elements in an aircraft
View Patent ↗A structure for use on an aircraft and a method of manufacturing said structure. The structure comprises first and second structural elements and a fastening device. The fastening device comprises a bolt that engages with a barrel nut. The first structural element is arranged, in use, to bear loads that are predominantly in a direction that is generally coplanar with the axis of the elongate member. The elongate member extends through the second structural element and ends inside the first structural element.
1. An aircraft structure comprising first and second structural elements joined by a fastening device, wherein
the fastening device comprises an elongate member and a securing member,
the first structural element is made at least partly of composite material,
the elongate member extends through the second structural element,
an end of the elongate member is secured inside the first structural element by the securing member, the securing member being at least partially embedded within the first structural element; and
the joint between the first structural element and the second structural element formed by the fastening device is in the form of a T-joint.
2. An aircraft structure according to claim 1 wherein the elongate member comprises a screw thread.
3. An aircraft structure according to claim 1 wherein the elongate member is a bolt.
4. An aircraft structure according to claim 3 wherein the securing member is a barrel nut.
5. An aircraft structure according to claim 1 wherein the securing member comprises a locking mechanism.
6. An aircraft structure according to claim 1 wherein the securing member extends transversely to the elongate member.
7. An aircraft structure according to claim 1 wherein the securing member is accommodated in a machined hole in the first structural element.
8. An aircraft structure according to claim 1 wherein the majority of the fibres of the composite fibre material are, in use, generally coplanar with the axis of the elongate member.
9. An aircraft structure according to claim 1 wherein the first structural element is in the general form of a substantially flat plate or bar.
10. An aircraft structure according to claim 1 wherein the first structural element is selected from the group consisting of a rib, a spar and a stringer.
11. An aircraft structure according to claim 1 wherein the second structural element is a wing skin.
12. An aircraft structure according to claim 1 wherein the first structural element is strengthened in the region of the elongate member.
13. An aircraft wing comprising first and second structural elements joined by a fastening device, wherein
the fastening device comprises an elongate member and a securing member,
the first structural element is made at least partly of composite material,
the elongate member extends through the second structural element,
an end of the elongate member is secured inside the first structural element by the securing member, the securing member being at least partially embedded within the first structural element; and
the joint between the first structural element and the second structural element formed by the fastening device is in the form of a T-joint.
14. A method of manufacturing an aircraft structure, the method including the step of fastening a first structural element to a second structural element by means of an elongate member that extends through the second structural element, and that has an end that is secured inside the first structural element by means of a securing member, wherein
the first structural element is made at least partly of composite material,
the securing member is at least partially embedded within the first structural element, and the joint between the first structural element and the second structural element formed by the fastening device is in the form of a T-joint.
15. A method according to claim 14 wherein the method includes a step of machining a hole in the first structural element and then inserting the securing member in the hole.
16. An aircraft structure according to claim 1 , wherein the T-joint is formed by a part of the first structural element and a part of the second structural element, the part of the first structural element extending substantially perpendicularly from the second structural element.