Cable way for aircraft with a structure made of composite material

• US 8,540,189 B2
• Filed: 09/22/2010
• Issued: 09/24/2013
• Est. Priority Date: 09/23/2009
• Status: Active Grant

• Current Assignee: Safran Electrical & Power
• Original Assignee: Labinal (Safran SA)
• Inventors: Ayme, Arnaud Camille, Roques, Serge Thierry
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Dixon, Keith L
• Application Number:
  US12/888,079
• Publication Number:
  US 20110068228A1
• Time in Patent Office: 1,098 Days
• Field of Search: 244/119, 244/129.2, 244/129.1, 244/131, 174/68.1, 174/68.3, 174/72.A, 174/72.R, 174/88.R, 174/70.C, 174/95
• US Class Current: 244/119
• CPC Class Codes: B64C 1/406 in combination with supports for lines, e.g. for pipes or cables
• CPC Class Codes: H02G 3/0418 Covers or lids; Their fastenings
• CPC Class Codes: H02G 3/0437 Channels

Abstract

A retention device, in the form of a trunking with a substantially U-shaped section, for retaining at least one cable running along the structure of an aircraft, fastened to said structure by a fastening device and providing an electrical continuity over the whole of its length is disclosed. The device is electrically connected to a current-return circuit from the items of equipment of the aircraft. The trunking includes at least one curve on its longitudinal axis corresponding substantially to that of a frame of a fuselage. It is intended to be mounted on a frame of an aircraft made of carbon fibers and to protect the skin of the aircraft against a possible contact with a damaged cable.

Claims

1. A cable retention device arranged to receive at least one cable, comprising:

a trunking extending along a longitudinal axis comprising at least one curve, said trunking including a metal portion ensuring an electrical continuity over an entire length thereof, and presenting a U-shaped cross section with first and second side walls and a bottom wall connecting said first and second side walls; and

a retaining stopper which cooperates with said trunking to hold said cable against said bottom wall of said trunking such that said cable is sandwiched between said bottom wall of said trunking and said stopper,

wherein a value of said curve of said trunking corresponds substantially to a curvature of frames of a fuselage of an aircraft, a radius of said curve being greater than one meter.

2. The retention device as claimed in claim 1, wherein the curve of the longitudinal axis is situated in the plane of the bottom of the trunking.

3. The retention device as claimed in claim 1, wherein the curve of the longitudinal axis is situated in a plane perpendicular to the bottom of the trunking.

4. The retention device as claimed in claim 1, wherein said stopper comprises two branches which extend along the side walls of the trunking and have an elasticity giving said branches a degree of freedom in a plane transverse to the longitudinal axis of the trunking.

5. The retention device as claimed in claim 4, wherein said stopper further comprises a central portion including lower face with a shape substantially corresponding to an external shape of the cable and an upper face to which lower portions of said branches are joined.

6. The retention device as claimed in claim 5, wherein said branches extend away from the central portion of said stopper.

7. The retention device as claimed in claim 4, wherein a face of said branches in contact with the side walls of the trunking has at least one non-return device which opposes withdrawal of the stopper after said stopper has been put in place.

8. The retention device as claimed in claim 4, wherein said branches have, at rest, a position diverging from one another so that the stopper exerts a pressure against the walls of the trunking when said stopper is inserted therein.

9. The retention device as claimed in claim 1, wherein the trunking comprises, on its outer face, lugs designed to provide the electrical connection of its metal portion to a current-return circuit of an aircraft.

10. An aircraft fuselage comprising at least one cable-retention device as claimed in claim 1.

11. The aircraft fuselage as claimed in claim 10, further comprising at least one structural portion made of carbon fibers.

12. The aircraft fuselage as claimed in claim 11, wherein at least one frame made of carbon fibers carries the retention device.

13. The aircraft fuselage as claimed in claim 11, wherein the retention device is fastened to stringers parallel to the frames of the aircraft.