Method for manufacturing a structural part made of a composite material and including a radially oriented double yoke

摘要

A method of fabricating an aircraft landing gear rocker beam comprising a body having a clevis (24) with two lugs (19, 21) parallel to a direction that is radial relative to the body, the method comprising the steps of: forming a first mandrel; applying one or more first braided fiber layers (11) on the first mandrel; fitting a second mandrel element on the assembly as constituted in this way, the second mandrel element extending between the two lugs (19, 21) of the clevis (24) that is to be formed; applying one or more second braided fiber layers (17) on the assembly as constituted in this way; injecting resin into the various layers (11, 17) and polymerizing the resin; and machining the resulting workpiece blank in order to cut away a region of the second braided layers (17) in order to separate the two lugs (19, 21) of the clevis (24) from each other.

主权项

1. A method of fabricating a structural element such as an aircraft landing gear rocker beam (28) out of composite material, the element comprising a body having a portion that extends along a longitudinal axis (AL) while presenting a cross-section that defines a closed outline while also being provided with a clevis (24) comprising two lugs (19, 21) that extend parallel to a radial direction relative to the longitudinal axis (AL), the clevis (24) being for receiving a pin that is oriented perpendicularly to the longitudinal axis (AL) while being spaced apart from said longitudinal axis (AL), the method comprising the steps of:
forming a first mandrel (9); applying one or more first braided fiber layers (11) on the first mandrel (9) by using a braiding machine (12) so that these layers extend all around the first mandrel (9) and all along its length; fitting a second mandrel element (16) on the assembly (9, 11) formed by the first mandrel (9) and each of the first layers (11) that it is carrying, the second mandrel element (16) extending in a region situated between the two lugs (19, 21) of the clevis (24) that is to be formed; applying one or more second braided fiber layers (17) on the assembly constituted by the first mandrel (9) with each of the first layers (11) that it carries together with the second mandrel element (16) fitted thereto; injecting the resin into the various fiber layers (11, 17) that have been applied, and polymerizing the resin in order to form a workpiece blank; machining the workpiece blank in the vicinity of the clevis that is to be made so as to cut away a region of each second layer (17) in order to separate the two lugs (19, 21) of the clevis (24) from each other; and making a hole in each lug (19, 21) of the clevis (24).