Structure of the load introduction zone in the rear end of...

B - Operations – Transporting – 64 – C

Patent

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B64C 1/26 (2006.01)

Patent

CA 2747690

Load introduction zone in the rear end of an aircraft comprising receiving elements (3, 4) of the loads of the horizontal and vertical tail stabilizers connected to structural elements (2, 8, 9) wherein: a) said structural elements are the cladding (8), two contiguous load-bearing frames (2) with a .PI. or omega cross-section and, at least, a third frame (9); b) the receiving element of the horizontal tail stabilizer load is a first fitting (3) structured as a torque box, transversely arranged between said load-bearing frames (2) and connected to them, and the receiving elements of the vertical tail stabilizer loads are some second fittings (4) coupled to these frames (2, 9); c) said frames (2, 9) and said first and second fittings (3, 4) are entirely made of composite material.

La présente invention concerne une structure de la zone d'introduction de charges dans le fuselage arrière d'un aéronef, laquelle structure comprend des éléments récepteurs (3, 4) des charges du stabilisateur horizontal et du stabilisateur vertical de queue reliés à des éléments structurels (2, 8, 9). Dans ladite structure : a) les éléments structurels sont le revêtement (8), deux couples de charge contigus (2) présentant une section transversale en forme de p ou d'oméga, ainsi qu'au moins un troisième couple (9); b) l'élément récepteur de la charge du stabilisateur horizontal de queue consiste en une première ferrure (3) présentant la structure d'un caisson de torsion, placée de façon transversale entre les couples de charge (2) et reliée à ceux-ci, et les éléments récepteurs des charges du stabilisateur vertical de queue consistent en des secondes ferrures (4) accouplées auxdits couples (2, 9); c) lesdits couples (2, 9) et lesdites premières et secondes ferrures (3, 4) étant réalisés intégralement en matériau composite.

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