Aircraft comprising a link rod one part of which is made of composite

Patent metadata

Field	Value
Publication number	US-9638241-B2
Application number	US-201113811802-A
Country	US
Kind code	B2
Filing date	Jul 18, 2011
Priority date	Jul 23, 2010
Publication date	May 2, 2017
Grant date	May 2, 2017

Abstract

The link for an aircraft comprises at least two portions respectively made of metal and of composite material together forming a common section of a middle segment of the link in a plane perpendicular to a longitudinal direction of the link.

First claim

What is claimed is:

1. A link for an aircraft, the link comprising:
at least two portions respectively made of metal and of composite material together forming a middle segment of the link with both being present in any section of the middle segment in a plane perpendicular to a longitudinal direction of the link, and
end parts located at opposite ends of the middle segment, the middle segment extending between the end parts,
wherein the at least two portions are spaced apart from each other in the middle segment by spacer elements engaging the end parts, whereby the two portions have no region of mutual contact,
wherein each of the end parts includes a connector configured to be connected to a structure or other part of the aircraft, at least one of the connectors including an inclined face arranged to urge a corresponding ring in abutment with a corresponding one of the spacer elements, which is prevented from sliding relative to the composite portion in either of two opposite longitudinal directions, and
wherein the at least two portions are arranged to face each other in the middle segment with no material whatsoever between them in the middle segment.

2. The link according to claim 1 , wherein one of the portions extends inside the other portion.

3. The link according to claim 1 , wherein the composite material portion extends inside the metal portion.

4. The link according to claim 1 , wherein each of the two portions is in the form of a body of revolution about a longitudinal axis of the link.

5. The link according to claim 2 , wherein the inner portion is hollow.

6. The link according to claim 2 , wherein the inner portion is solid.

7. The link according to claim 1 having at least one of the end parts fastened to the portions without coming directly into contact with either of them.

8. The link according to claim 1 , wherein the metal portion is mounted to be slidably movable relative to an end of the link in the longitudinal direction locally away from said end, the link having an abutment against the metal portion sliding in the opposite direction.

9. The link according to claim 1 , wherein the connector urging the corresponding ring in abutment with the at least one spacer bears against the ring via a face that is inclined relative to a longitudinal axis of the link.

10. The link according to claim 9 , wherein the end part is a clevis.

11. The link according to claim 9 , wherein each of the end parts is a nut that is distinct from the end part of the link and that is screwed onto a spacer interposed between the metal and composite material portions radially relative to a longitudinal axis of the link.

12. The link according to claim 1 , arranged in such a manner that the composite material portion is subjected in the middle segment to tension stress in the longitudinal direction when the link is at rest.

13. An aircraft including a plurality of links according to claim 1 , the plurality of links together forming a trellis structure, wherein the links are identical to one another and they are distributed in several groups of links, the links in each group being coplanar, mutually parallel and spaced apart from one another, the links from different groups being in different planes.

14. A link for an aircraft comprising:
a middle body having an axis and including a metal sleeve enclosing and coaxial with a composite material beam, wherein the metal sleeve and composite material beam both extend an entire length of the middle body;
spacer elements between the metal sleeve and the composite material beam, wherein the spacer elements form a gap between the metal sleeve and the composite material beam which extends the entire length of the middle body, and
end parts at opposite ends of the middle body and aligned with the axis of the middle body, the middle body extending between the end parts, wherein each of the end parts includes a connector configured to be connected to a structure or other part of the aircraft,
at least one connector including an inclined face arranged to urge a corresponding ring in abutment with a corresponding one of the spacer elements, which is prevented from sliding relative to the composite portion in either of two opposite longitudinal directions, and
wherein the metal sleeve and composite material beam are arranged so as to be spaced apart and facing each other in the middle body with no material whatsoever between them in the middle body.

15. The link of claim 14 wherein the composite material beam is a hollow tube having a circular cross section.

16. The link of claim 14 wherein the spacer element includes a radially inward surface abutting an outer surface of the composite tube and an radially outward surface abutting a radially inward surface of the metal sleeve.

17. A link for an aircraft, the link comprising:
a middle segment comprising a portion made of metal and a portion made of composite material;
connectors located at opposite ends of the middle segment, the middle segment extending between the connectors; and
a plurality of spacers separating the two metal and composite portions from each other so as to form a gap between the two portions with no region of mutual contact between the two portions;
the plurality of spacers being rigidly fastened to the connectors and the composite portion and slidably engaging the metal portion, whereby any axial traction force applied to the connectors is transmitted to the spacers and the composite portion and not to the metal portion so that only the composite tube withstands the axial traction force;
each of the connectors including a corresponding face arranged to urge a corresponding ring in abutment with a corresponding one of the plurality of spacers when a compression force is applied to the connector, each of the spacers including a shoulder which slidably engages the metal portion when the compression force is applied to the connectors and thus transmitted to the corresponding spacers, whereby both the composite portion and the metal portion withstand the compression force.

18. A link for an aircraft, the link comprising:
a middle segment comprising a portion made of metal and a portion made of composite material;
connectors located at opposite ends of the middle segment, the middle segment extending between the connectors; and
a plurality of spacers separating the two metal and composite portions from each other so as to form a gap between the two portions with no region of mutual contact between the two portions;
each of the connectors being threaded onto a corresponding one of the plurality of spacers and having a frustoconical face arranged to come into surface-on-surface contact against a corresponding ring which is in abutment with the corresponding spacer, the corresponding spacer making surface-on-surface contact with the composite portion and slidably engaging the metal portion so that each connector, its corresponding spacer and ring and the composite portion are rigidly fastened together
whereby any axial traction force applied to the connectors is transmitted to the spacers and the composite portion and not the metal portion so that only the composite portion withstands the axial traction force; and
whereby, when a compression force is applied to the connectors and thus transmitted to the spacers, both the composite portion and the metal portion withstand the compression force.

19. A link for an aircraft, the link comprising:
at least two portions respectively made of metal and of composite material, together forming a

Assignees

• Gallant Guillaume
• Guillemaut Julien
• Airbus Operations Sas

Inventors

• Gallant Guillaume
• Guillemaut Julien

Classifications

• F16C7/02 Primary

  Constructions of connecting-rods with constant length · CPC title

• Y10T29/49826

  Assembling or joining · CPC title

• Y10T74/2144

  Yieldable · CPC title

• G01D21/00

  Measuring or testing not otherwise provided for · CPC title

• F16C7/026

  made of fibre reinforced resin · CPC title