Method of joining structural elements in an aircraft
AssigneeAirbus UK Limited
InventorMichael Stephens
Life of this patent
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Abstract
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.
Claims22
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 elongate member presenting an axis,
- the first structural element is made at least partly of composite material and is arranged, in use, to bear loads that are predominantly in directions that are generally coplanar with the axis of the elongate member,
- the elongate member extends through the second structural element, and
- an end of the elongate member is secured inside the first structural element by the securing member.
An aircraft wing comprising a wing skin and a first structural element inside the wing that supports the wing skin, wherein
- the wing skin is joined to the first structural element by a bolt and barrel nut,
- the bolt extending through the wing skin and having an end that is secured inside the first structural element by the barrel nut,
- the first structural element being made at least partly of composite material having layers of fibre material arranged in plies that are generally coplanar with the axis of the bolt.
An aircraft wing comprising a wing skin and a first structural element inside the wing that supports the wing skin, wherein
- the wing skin is joined to the first structural element by a bolt and barrel nut,
- the bolt extending through the wing skin and having an end that is secured inside the first structural element by the barrel nut,
- the first structural element being made at least partly of composite material, and
- the joint between the first and second structural elements being in the form of a T-joint.
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 elongate member presenting an axis,
- the first structural element is made at least partly of composite material and is arranged, in use, to bear loads that are predominantly in directions that are generally coplanar with the axis of the elongate member,
- the elongate member extends through the second structural element, and
- an end of the elongate member is secured inside the first structural element by the securing member.
An aircraft including 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 elongate member presenting an axis,
- the first structural element is made at least partly of composite material and is arranged, in use, to bear loads that are predominantly in directions that are generally coplanar with the axis of the elongate member,
- the elongate member extends through the second structural element, and
- an end of the elongate member is secured inside the first structural element by the securing member.
A kit of parts including a first structural element made at least partly of composite material, a second structural element, and a fastening device comprising an elongate member and a securing member, the elongate member presenting an axis, the kit of parts being capable of building an aircraft structure, comprising the first and second structural elements joined by the fastening device, in such a way that the first structural element is arranged, in use, to bear loads that are predominantly in directions that are generally coplanar with the axis of the elongate member, the elongate member extends through the second structural element, and an end of the elongate member is secured inside the first structural element by the securing member.
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 and is arranged for bearing loads that are predominantly in directions that are generally coplanar with the axis of the elongate member.
Dependencies are inferred from the claim text.