Patent ID: 8613405

Claim:
An assembly for an aircraft comprising: a wing element; a turbomachine; and an attachment strut for attaching the turbomachine on the wing element, the attachment strut comprising a primary structure for passage of forces and attachment means for attaching the primary structure on the wing element, forming an isostatic system; the attachment means comprising: a first attachment or a first group of attachments housed in a leading edge of the wing element, and configured to ensure only reaction of the forces exerted in a transverse direction of the turbomachine and in a longitudinal direction thereof; a second attachment housed in the leading edge of the wing element, offset in the transverse direction of the first attachment or the first group of attachments, and configured to ensure reaction only of the forces exerted in the longitudinal direction of the turbomachine; a third attachment or a third group of attachments offset in a vertical direction of the first attachment or the first group of attachments and the second attachment, and configured to react to only the forces exerted in the transverse direction of the turbomachine and in the vertical direction thereof; and a fourth attachment comprising a connecting rod extending backward, a first end of which is connected on the primary structure and a second end of which is connected on the wing element, the first connecting rod end being offset in the vertical direction of the first attachment or the first group of attachments.