Fastening system for fastening a component on a fuselage structure

Patent metadata

Field	Value
Publication number	US-11136124-B2
Application number	US-201816222457-A
Country	US
Kind code	B2
Filing date	Dec 17, 2018
Priority date	Dec 22, 2017
Publication date	Oct 5, 2021
Grant date	Oct 5, 2021

Abstract

A system has a frame with first and second spaced apart edges, a first holder couplable to the fuselage structure and embodied for articulated connection to a first region of the frame that is close to the first edge, a second holder couplable to the fuselage structure, and a strut. A first end of the strut is connectable in an articulated manner to the second holder. A second end of the strut is connectable in an articulated manner to a second region of the frame near the second edge and remote from the first edge. The frame and the strut form a triangular structure with the first and second holders. The strut and the frame form two sides of the triangular structure. A length of the first and/or second side is variable to adjust the position of the frame.

First claim

What is claimed is:

1. A fastening system for fastening components on a fuselage structure in an interior of an aircraft, the fastening system comprising:
a holding frame with a first edge and a second edge spaced apart from the first edge;
at least one first holder, which can be coupled to the fuselage structure and is embodied for articulated connection to the holding frame in a first region of the holding frame, said region being close to the first edge;
at least one second holder, which can be coupled to the fuselage structure; and
at least one holding strut, a first end of which can be connected in an articulated manner to the second holder and a second end of which can be connected in an articulated manner to the holding frame in a second region adjacent to the second edge and remote from the first edge;
wherein the holding frame, the holding strut, the first holder, and the second holder are configured to form a triangular structure with the first and second holder, which are arranged spaced apart from one another along a circumferential direction of the fuselage structure;
wherein the holding strut and the holding frame form a first side and a second side of the triangular structure; and
wherein at least one of the holding frame, the holding strut, the first holder and the second holder is designed to variably set a length of the first side and/or of the second side in order to adjust the position of the holding frame.

2. The fastening system according to claim 1 , further comprising at least one elongate base body, wherein the at least one elongate base body is fastenable on a plurality of first and/or second holders and is configured to introduce a force acting along an axis of extent of the base body into a plurality of first and/or second holders.

3. The fastening system according to claim 2 , wherein the first holders and the second holders are configured to rigidly retain the respective base body.

4. The fastening system according to claim 1 , wherein the first base body and the second base body are each configured as a tube.

5. The fastening system according to claim 1 , wherein the first holder is configured to set an adjustable spacing between the first region of the holding frame and the first holder.

6. The fastening system according to claim 5 , wherein:
the first holder has a first connector with an opening that has a first tooth system in some region or regions, and a second connector with an elongate body that has a second toothing in some region or regions; and
in a first alignment with respect to the opening of the first connector, the elongate body is insertable into said opening and, by rotation into a second alignment, establishes a positive joint between the first tooth system and the second tooth system.

7. The fastening system according to claim 6 , further comprising a decoupling component made from a plastic, which surrounds the first connector at least partially in the form of a ring.

8. The fastening system according to claim 1 , wherein
the holding strut or the second holder has a first connector with an opening that has a first tooth system in some region or regions, and a second connector with an elongate body that has a second tooth system in some region or regions, wherein, in a first alignment with respect to the opening of the first connector, the elongate body is insertable into said opening and, by rotation into a second alignment, establishes a positive joint between the first tooth system and the second tooth system.

9. The fastening system according to claim 1 , further comprising at least one tolerance compensating device, which is arranged in the second region of the holding frame, wherein the tolerance compensating device is connectable to the holding strut and is configured to shift and lock a connecting position of the holding strut on the holding frame between the second edge and the first edge.

10. The fastening system according to claim 9 , wherein:
the tolerance compensating device has a slide, which is pivotably connected to the holding strut, and an elongate depression, which is arranged on the holding frame and has a slideway extending along the extent of the depression to provide sliding guidance for the slide;
the depression and the slide are each provided with a first tooth system in some region or regions; and
an elongate locking element with a second tooth system in some region or regions is positioned in the depression and is configured to establish a positive joint between the first tooth system and the second tooth system in a first alignment, such that the position of the slide on the slideway is locked, and to release the positive joint in a second alignment.

11. The aircraft according to claim 10 , wherein the fuselage has a longitudinal axis, a right-hand side, a left-hand side, and at least one elongate base body on each side of the fuselage along a significant part of the fuselage.

12. The aircraft according to claim 11 , further comprising at least one monument and at least one monument holder, wherein the monument stands on a floor arranged in the fuselage and is connected by the at least one monument holder, by means of a monument section spaced apart from the floor, to one of the base bodies.

13. The aircraft according to claim 11 , wherein the monument holder comprises an elongate strut connected by one end to the section of the relevant holder which is spaced apart from the monument along the longitudinal axis and by another end to the monument.

14. An aircraft comprising:
a fuselage with a fuselage structure;
a fastening system according to claim 1 ; and
at least one component fastened on the fuselage structure by the fastening system.

15. The aircraft according to claim 14 , wherein the component is a service unit for passengers or an overhead storage bin.

Assignees

• Airbus Operations Gmbh

Inventors

• Benthien Hermann

Classifications

• B64D47/00

  Equipment not otherwise provided for · CPC title

• B64D11/003 Primary

  Stowage devices for passengers' personal luggage · CPC title

• F16B5/0614

  in angled relationship · CPC title

• B64C1/00

  Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like · CPC title

• B64F5/00

  Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for · CPC title