Abstract: A rear frame of an air intake of a nacelle of an aircraft, is made in part of composite material that is based on a fiber-reinforced geopolymer resin and includes at least one part (56) that encompasses an orifice that is provided for the passage of a defrosting system that is made of composite material that is based on a fiber-reinforced geopolymer resin and at least one other metal part (58).

Abstract: A propulsion unit includes at least one exhaust pipe (62, 76) that includes an air discharge that is delimited by a trailing edge (78, 82). The end part of the exhaust pipe (62, 76) includes two scalloped shapes (84) that each correspond to a preferred acoustic radiation direction, separated by advanced parts (86) that can limit the acoustic radiation, whereby the scalloped shapes are offset upward relative to the horizontal median plane.

Abstract: The object of the invention is a pipe that is integrated into the aircraft piping, characterized in that it is produced from a composite material that comprises a fiber-reinforced geopolymer resin matrix.

Abstract: A beam for reinforcing the structure of an aircraft is located inside the fuselage of the aircraft. The fuselage includes at least one pressurized zone (P) that is separated by at least one airtight wall (18) of at least one other non-pressurized zone (16), the beam and the at least one airtight wall being intersecting. The beam traverses the at least one airtight wall (18) that includes a cutaway that is adapted to the section of the beam, whereby sealing elements (30) are provided to ensure the sealing between the beam and the airtight wall (18) that is traversed.

Abstract: An articulation device connects a door (46) of an aircraft nacelle (30), the nacelle (30) including an external wall called a fairing including at least one opening (44) adapted to be closed by at least the door (46). The articulation device includes at least one arm (56) connected by a first pivotal axle (58) to the nacelle (30) and by a second pivotal axle (60) to the door (46), the two pivotal axles (58, 60) being substantially parallel.

Abstract: A milling tool has a cutting edge geometry with a main cutting edge, a cutting corner, optionally with a bordering planar cutting edge segment, and a secondary cutting edge. The tool is used for milling to achieve the smoothest level surface possible parallel to the rotational axis of the milling tool. Each main cutting edge is formed to result in a generatrix of the envelope curve described by the rotation of the milling tool that has a first outwardly curving segment and a second inwardly curving segment. The first segment increases in its distance from the rotational axis from the beginning of the segment to the end of the segment. The distance of the second segment decreases from its beginning towards its end. The tangents at each point of the second segment encompass an angle ?2 of more than 0° and up to 3° with a parallel to the rotational axis.

Abstract: A milling tool has a cutting edge geometry with a main cutting edge, a cutting corner, optionally with a bordering planar cutting edge segment, and a secondary cutting edge. The tool is used for milling to achieve the smoothest level surface possible parallel to the rotational axis of the milling tool. Each main cutting edge is formed to result in a generatrix of the envelope curve described by the rotation of the milling tool that has a first outwardly curving segment and a second inwardly curving segment. The first segment increases in its distance from the rotational axis from the beginning of the segment to the end of the segment. The distance of the second segment decreases from its beginning towards its end. The tangents at each point of the second segment encompass an angle &agr;2 of more than 0° and up to 3° with a parallel to the rotational axis.