A pressure bulkhead (10; 10') of fibre composite material for an aircraft fuselage (6) for the pressure-tight axial closure of a fuselage region (8) configured to be put under internal pressure comprises a first area element (14; 14'), at least one second area element (22; 22') and a plurality of core elements (16; 16'). The first area element (14; 14') has a plurality of receptacles (12; 12'). Each receptacle (12; 12') is configured to receive a core element (16; 16'). The core elements (16; 16') are received in the receptacles (12; 12') between surfaces facing one another of the first area element (14; 14') and of the at least one second area element (22; 22'). The surfaces facing one another of the first area element (14; 14') and of the at least one second area element (22; 22') are connected to one another in regions (20; 20') without core elements.
Pressure bulkhead for an aircraft
Druckschott für ein Flugzeug
Cloison de pressurisation pour avion
08.04.2020
Patent
Elektronische Ressource
Englisch
Pressure bulkhead for an aircraft fuselage, and an aircraft comprising such a pressure bulkhead
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