Structure, especially a fuselage structure of an aircraft or...

B - Operations – Transporting – 64 – C

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Details

B64C 1/10 (2006.01)

Patent

CA 2703188

The present invention provides a fuselage structure (1; 1') of an aircraft comprising an annular skin segment (2; 2') which has a cross-sectional opening (3; 3'), a pressure cap (4; 4') for a pressure-tight closure of the cross-sectional opening (3; 3'), and a plurality of tension struts (7, 8, 9; 7', 8', 9') which in each case connect the pressure cap (4; 4') to the annular skin segment (2; 2') and absorb loads acting on the pressure cap (4; 4'), as tensile loads. This advantageously means that the tension struts (7, 8, 9; 7', 8', 9') do not have to absorb substantially any bending moments. Consequently, the tension struts can be produced with a relatively small cross section, which entails a reduction in weight. Furthermore, it is possible to produce and mount tension struts (7, 8, 9; 7', 8', 9') of this type in a simple manner.

La présente invention concerne une structure de fuselage (1; 1') d'un avion, cette structure comprenant un segment de revêtement annulaire (2; 2') présentant une ouverture de section (3; 3'), une calotte étanche (4; 4') destinée à obturer cette ouverture de section (3; 3') de façon étanche, ainsi que plusieurs tirants (7, 8, 9; 7', 8', 9') qui relient la calotte étanche (4; 4') au segment de revêtement annulaire (2; 2') et absorbent les charges qui s'exercent sur la calotte étanche (4; 4') sous forme de charges de traction. L'avantage de cette configuration est que les tirants (7, 8, 9; 7', 8', 9') ne doivent absorber sensiblement aucun couple de flexion, ce qui permet de les concevoir avec une section réduite et ainsi avec un poids réduit. De tels tirants (7, 8, 9; 7, 8, 9) sont également faciles à produire et à monter.

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