Patent ID: 9387623
Filing Date: 2016-07-12
CPC Classification: B29C,B29K,B64C,F16C

Claim Text:
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 ( applying one or more first braided fiber layers ( fitting a second mandrel element ( applying one or more second braided fiber layers ( injecting the resin into the various fiber layers ( 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 ( making a hole in each lug (