Structural assembly of a part of an aircraft, in particular...

B - Operations – Transporting – 64 – C

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Details

B64C 1/00 (2006.01) B64C 1/12 (2006.01) B64C 1/18 (2006.01) B64C 1/40 (2006.01)

Patent

CA 2397191

The structural assembly comprises an external structure (3) equipped with a floor (4), an enclosing assembly (5) comprising enclosing panels (6) forming a self-supporting envelope (7) which is associated inside (9) the external structure (3) and mounted on the floor (4), and a linkage system (10) to link the self-supporting envelope (7) with the external structure (3). The linkage system (10) comprises a plurality of linkage means (11) which fasten, by means of rigid and permanent links, the self-supporting envelope (7) to the external structure (3) and effect this rigid and permanent fastening exclusively between the floor (4) of the external structure (3) and some extremities (12) of enclosing panels (6) of the self-supporting envelope (7).

L'ensemble structurel comporte une structure externe (3) munie d'un plancher (4), un ensemble d'habillage (5) comprenant des panneaux d'habillage (6) formant une enveloppe autoporteuse (7) qui est agencée à l'intérieur (9) de la structure externe (3) et montée sur le plancher (4), et un système de liaison (10) pour lier l'enveloppe autoporteuse (7) à la structure externe (3). Le système de liaison (10) comporte une pluralité de moyens de liaison (11) qui fixent, par des liaisons rigides et 0 permanentes, l'enveloppe autoporteuse (7) à la structure externe (3) et réalisent cette fixation rigide et permanente exclusivement entre le plancher (4) de la structure externe (3) et des extrémités (12) de panneaux d'habillage (6) de l'enveloppe autoporteuse (7).

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