Abstract: A method for manufacturing a tool equipment used in molding a panel for a fuselage of an aircraft from a composite material is provided. The method includes manufacturing a mold such that a fixed part includes a hub and an intermediary member. A plurality of removable modules which are able to be mounted on this fixed part are also manufactured and then fastened to the fixed part so as to modify an external surface upon which composite material is laid-up or draped during the molding of the panel.

Abstract: An aircraft front portion includes a sealed bulkhead separating a non pressurized radome area from a pressurized area. The sealed bulkhead is delimited by two surfaces opposite to each other, one being substantially concave when seen from the radome area and the other being substantially convex when seen from the pressurized area.

Abstract: A tool equipment for manufacturing a panel in a composite material, in particular for an aircraft fuselage. The tool equipment (1) comprises a mould (2) including a fixed part (4) and a plurality of removable modules (6) which are able to be mounted on this fixed part (4).

Abstract: A cigarette includes a rod comprising a wrapped tobacco column that is joined to an axially aligned filter by a band of air impermeable tipping paper. The filter end of the rod is inserted into a mouthpiece having an air impermeable outer surface that comprises a ventilation tube and a second filter, separated by a mixing chamber. The ventilation tube has an air permeable annular wall that defines a central axial passage through which the rod extends. In use, the end surface of the annular wall at the rod end of the ventilation tube, which extends radially outward around the rod, acts as a ventilation surface through which air is drawn into the mixing chamber, where it mixes with mainstream smoke from the burning tobacco rod. The air/smoke mixture is drawn through the second filter into the consumer's mouth.

Abstract: The invention relates to an aircraft front portion (1) including a sealed bulkhead (10) separating a non-pressurized radome area (20) from a pressurized area (30), whereof the volume of the pressurized area (30) is optimized. For this, said sealed bulkhead (10) is delimited by two surfaces (11,12) opposite to each other, one (11) being substantially concave when it is seen from said radome area (20) and the other one (12) being substantially convex when it is seen from said pressurized area (30).

Abstract: The disclosed embodiments relate essentially to a primary structure of an aircraft fuselage that has at least a first strut linked at one end to a crossbeam and at the other end to a reinforcing frame. A second strut has one end fastened to the structure below the end of the first strut, and another end linked to the first strut through an intermediate sliding linkage. A deformable member is linked to the struts so that in case of a crash, the compressive forces press against the second strut, so that the end of the second strut slides along the first strut so as to stretch the deformable member longitudinally to absorb the shock.