Abstract: A pressurized aircraft fuselage includes a pressure bulkhead installed on a fuselage structure, which forms a barrier between an internal pressurized cabin area and an outside area, wherein the edge of the pressure bulkhead is circumferentially attached to the fuselage structure by fastening means, wherein the fastening means include a pair of ring-shaped attachment frames made of an open or hollow profile, which are disposed at each side of the pressure bulkhead respectively, in order to form a clamping connection for the pressure bulkhead towards the fuselage structure.

Abstract: An energy-absorbing connection arrangement with a multitude of connectors for joining two components, such as a transverse member and a circular frame element, of an aircraft fuselage. Each connector comprises a headed shaft and the shafts reach through component boreholes. On the shaft ends facing away from the heads, counter-bearings are provided. At least one of the components comprises a fiber-reinforced plastic material. A head and/or counter-bearing of at least one connector rests against at least one underlay device. The underlay device is received in a guide groove in the first component, with the guide groove commencing in the region of the boreholes. The underlay device, upon exceeding a mechanical threshold load, is slidable away from the boreholes. Energy absorption takes place along a longitudinal center axis of the guide groove as a result of hole-bearing-stress failure and/or the shearing of the fiber-reinforced plastic material component.

Abstract: An energy-absorbing connection arrangement with a multitude of connectors for joining two components, such as a transverse member and a circular frame element, of an aircraft fuselage. Each connector comprises a headed shaft and the shafts reach through component boreholes. On the shaft ends facing away from the heads, counter-bearings are provided. At least one of the components comprises a fiber-reinforced plastic material. A head and/or counter-bearing of at least one connector rests against at least one underlay device. The underlay device is received in a guide groove in the first component, with the guide groove commencing in the region of the boreholes. The underlay device, upon exceeding a mechanical threshold load, is slidable away from the boreholes. Energy absorption takes place along a longitudinal center axis of the guide groove as a result of hole-bearing-stress failure and/or the shearing of the fiber-reinforced plastic material component.

Abstract: A pressurized fuselage of an aircraft includes a fuselage structure and a pressure bulkhead mounted therein for forming a fuselage-internal pressure region. The pressure bulkhead is attached on the edge region, by way of mounting means, to the inside of the fuselage structure. The mounting means comprise at least one pivoting socket arrangement, arranged on the edge side of the pressure bulkhead, which edge side faces away from the pressure region, and interacts with the fuselage structure, as well as a supporting frame element, arranged on the opposite edge side and supporting itself on the fuselage structure.

Abstract: A pressurized aircraft fuselage includes a pressure bulkhead installed on a fuselage structure, which forms a barrier between an internal pressurized cabin area and an outside area, wherein the edge of the pressure bulkhead is circumferentially attached to the fuselage structure by fastening means, wherein the fastening means include a pair of ring-shaped attachment frames made of an open or hollow profile, which are disposed at each side of the pressure bulkhead respectively, in order to form a clamping connection for the pressure bulkhead towards the fuselage structure.

Abstract: An aircraft fuselage shell is fabricated of a double-walled composite structural component, including a core element bonded and sandwiched between an inner cover layer and an outer cover layer. The inner cover layer forms the main load bearing fuselage inner skin, and the outer cover layer forms the fuselage outer skin which carries a smaller proportion of the loads. The core element may consist of fiber-reinforced composite material while the cover layers may consist of an aluminum alloy, another metal, or fiber-reinforced composite material. The core element is air permeable and has air flow channels extending longitudinally therethrough in at least one direction. The cover layers do not seal or enclose the core element, so the core element is ventilatable. A ventilating airflow carries moisture as water vapor out of the core element, and then the moisture is condensed and removed by a moisture management unit.

Abstract: An aircraft fuselage shell is fabricated of a double-walled composite structural component, including a core element bonded and sandwiched between an inner cover layer and an outer cover layer. The inner cover layer forms the main load bearing fuselage inner skin, and the outer cover layer forms the fuselage outer skin which carries a smaller proportion of the loads. The core element may consist of fiber-reinforced composite material while the cover layers may consist of an aluminum alloy, another metal, or fiber-reinforced composite material. The core element is air permeable and has air flow channels extending longitudinally therethrough in at least one direction. The cover layers do not seal or enclose the core element, so the core element is ventilatable. A ventilating airflow carries moisture as water vapor out of the core element, and then the moisture is condensed and removed by a moisture management unit.