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

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.

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.

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.

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, and
• wherein the two portions are spaced apart from each other in the middle segment and have no region of mutual contact, the distance between the two portions being constant over a majority of the length of the link, and
• 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 spacer element serving to space apart the two portions from each other, the spacer element making surface-on-surface contact with the composite material portion so as to be prevented from sliding relative to the composite material portion in either of two opposite longitudinal directions.