Pressure bulkhead for an aircraft

摘要

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.