Abstract: An aircraft including a wing, a fuselage and at least one brace extending between the wing and the fuselage. The brace houses at least one fluid transfer line between the wing and the fuselage, such as an engine air bleed line, a hydraulic line or a fuel pipe. Use in particular to equip high-winged aircraft.

Abstract: In order to simplify the connection of a door to the outer envelope of an aircraft cell, it is provided to dispose the door into a portion of the outer envelope having tilted sides, as is the case at the nose cones and the tail cones of conventional airplanes, and in various portions of blended wing body airplanes and flying wings. Thus, the door can be configured to displace, in rectilinear translation, from one of its extreme opening and closing positions to the other, without requiring that the door protrudes outside of the outer envelope in the closing position.

Abstract: An aircraft of flying wing or blended wing body type comprising, for access to a pressurized housing, a non-pressurized door in the trailing edge of the aircraft and a pressurized door on the pressurized housing. The distance between the center of the pressurized door and a plane of symmetry of the aircraft is less than or equal to the distance between the center of the non-pressurized door and the plane of symmetry, and the pressurized door is located on a wall other than a rear wall of the pressurized housing or upstream of a rear extremum point of the housing in the absence of any such rear wall.

Abstract: An aircraft cockpit module (10) that incorporates, on the one hand, a single pilot seat (12) and, on the other hand, at least a part of the piloting equipment and controls necessary for flying an aircraft, the module (10). The aircraft cockpit module forms an assembly which can be moved unitarily and to be incorporated in a single operation in an aircraft cockpit. The module is dedicated to a single pilot and makes it possible to simplify the integration of the cockpit.

Abstract: An aircraft of flying wing or blended wing body type comprising, for access to a pressurized housing, a non-pressurized door in the trailing edge of the aircraft and a pressurized door on the pressurized housing. The distance between the center of the pressurized door and a plane of symmetry of the aircraft is less than or equal to the distance between the center of the non-pressurized door and the plane of symmetry, and the pressurized door is outside a rear wall of the pressurized housing or upstream of a rear extremum point of the housing in the absence of any such rear wall. This aircraft has optimum aerodynamic performance and the circulation of passengers between the pressurized housing and the exterior of the aircraft may be fluid.

Abstract: In order to simplify the connection of a door to the outer envelope of an aircraft cell, it is provided to dispose the door into a portion of the outer envelope having tilted sides, as is the case at the nose cones and the tail cones of conventional airplanes, and in various portions of blended wing body airplanes and flying wings. Thus, the door can be configured to displace, in rectilinear translation, from one of its extreme opening and closing positions to the other, without requiring that the door protrudes outside of the outer envelope in the closing position.

Abstract: A flying wing or blended body aircraft comprising at least one door installed in the leading edge of the aircraft. The lateral edges of the door extend each in a plane parallel to the plane of symmetry of the aircraft, when the door is closed. It reduces the aerodynamic penalties of a door installed in the leading edge of such an aircraft. It also reduces noise related to airflow at the door, and improves the robustness of the aircraft with respect to impacts.

Abstract: An aircraft including a wing, a fuselage and at least one brace extending between the wing and the fuselage. The brace houses at least one fluid transfer line between the wing and the fuselage, such as an engine air bleed line, a hydraulic line or a fuel pipe. Use in particular to equip high-winged aircraft.

Abstract: A propulsive system for aircraft that has a jet engine and a nacelle surrounding the aforementioned jet engine. The nacelle has a front section fixed relative to the jet engine, and a rear extremity behind the front section, and has a rear section with two petals hinged relative to the front section. Each of the two petals in a position called zero-setting forms an extension of the front section of the nacelle in which the inside and outside surfaces of the petals and, respectively, determine the aerodynamic forms of the rear section, which are in geometric continuity with the inside and outside surfaces and, respectively, that determine the aerodynamic forms of the front section. The petals can be set individually at a positive or negative setting angle to put into play the reverser, APU, air brake, vectorial, and taxiing modes of the propulsive system.

Abstract: An aircraft including a fuselage which extends along a longitudinal axis. The fuselage includes a substantially cylindrical central portion and a rear portion that may have a flattened or conventional shape. This rear portion which comprises the rear end of the fuselage includes a support surface which bears at least one horizontal stabilizer and/or vertical stabilizer. The rear portion is able to pivot in relation to the central portion around an axis such as the pitch axis, at least one stabilizer or the support surface being equipped with at least one control surface.

Abstract: An airplane, including a fuselage having an elongate shape along a longitudinal axis of the airplane, and at least one wing attached to the fuselage between front and back ends of the fuselage and a substantially cylindrical central portion and a rear scaleable portion on which a vertical tail assembly and a rear propulsion assembly are attached. Between a section for connecting the rear portion to the central portion of the fuselage and the back end: the maximum width of each fuselage section is constant or increases towards the rear up to a maximum fuselage width L; the height of each fuselage section decreases towards the rear, such that the back end of the fuselage forms a thin trailing edge substantially horizontal in the indicating line of the airplane and substantially rectilinear; a reactor for the propulsion assembly is provided in a so-called semi-buried configuration in the fuselage.

Abstract: An aircraft has a fuselage of elongated form along a longitudinal axis X corresponding essentially to the longitudinal axis of the aircraft. In a first forward section, the fuselage includes a cockpit in front of a cockpit bulkhead and a front landing gear associated with a landing gear compartment located behind the cockpit bulkhead. The front landing gear and the landing gear compartment are at least partially beneath a floorboard of a compartment of a lower space of the fuselage and in a bulge that increases a volume available for installation of the landing gear.

Abstract: An aircraft comprises: a fuselage; a front pair of wings; a rear pair of wings; and a pair of bodies, each body interconnecting, at a distance from the fuselage, the front and rear wings that are situated on the same side of the fuselage.

Abstract: The invention relates to an aircraft the fuselage (2) of which extends along a longitudinal axis. The fuselage includes a more or less cylindrical central portion (3) and a rear portion (4) that may have a flattened or conventional shape. This rear portion (4) which comprises the rear end of the fuselage includes a support surface (6) which bears at least one horizontal stabilizer (8) and/or vertical stabilizer (10). This is able to pivot in relation in relation to the central portion (3) around an axis such as the pitch axis, at least one stabilizer (8, 10) or the support surface (6) being equipped with at least one control surface (12a-b, 14a-b, 7).

Abstract: An aircraft fuselage with a shape elongated along a longitudinal axis X along a longitudinal axis of the aircraft that determines a direction toward the front along a direction of motion of the aircraft in flight. A front section with straight cross sections widening relative to the X axis, located at the front of the fuselage and ending in the front of the fuselage in a fuselage nose, and delimited at the rear by a cross section for joining to a rear part of the fuselage behind the front section. The front section includes a cockpit located above a floorboard between a cockpit bulkhead to the rear and a front base to the front.

Abstract: The airplane comprises a fuselage having frames, and at least two undercarriages each comprising a support and at least one wheel, the support being carried directly by the fuselage and being hinged to the fuselage about an axis that lies outside the frames. The undercarriage is movable between an operational position in which the or each wheel is vertical, and a rest position. The support and the wheel have a configuration such that, in the rest position, the undercarriage extends circumferentially relative to the fuselage and outside the frames.

Abstract: An airplane includes a fuselage having a shape elongated along a longitudinal axis X of the airplane and at least one wing fixed to the fuselage between the front end and the rear end of the fuselage. The fuselage includes a substantially cylindrical central part and a rear tapered part on which a vertical empennage is fixed. Between a section connecting the rear part with the central part of the fuselage and the rear end the maximum width of each section of the fuselage is constant or increasing rearwards up to a maximum width L of the fuselage, the height of each section of the fuselage is decreasing rearwards in the direction of the negative X, so that the rear end of the fuselage forms a trailing edge having a small thickness which is substantially horizontal in an airplane reference system and substantially rectilinear.

Abstract: An airplane, including a fuselage having an elongate shape along a longitudinal axis of the airplane, and at least one wing attached to the fuselage between front and back ends of the fuselage and a substantially cylindrical central portion and a rear scaleable portion on which a vertical tail assembly and a rear propulsion assembly are attached. Between a section for connecting the rear portion to the central portion of the fuselage and the back end: the maximum width of each fuselage section is constant or increases towards the rear up to a maximum fuselage width L; the height of each fuselage section decreases towards the rear, such that the back end of the fuselage forms a thin trailing edge substantially horizontal in the indicating line of the airplane and substantially rectilinear; a reactor for the propulsion assembly is provided in a so-called semi-buried configuration in the fuselage.

Abstract: A multi-engine aircraft includes at least two first engines and a third engine located at a rear part of the fuselage, containing rear tail sections, along a vertical longitudinal plane of symmetry of the fuselage. The rear tail sections define a channel which is symmetrical with respect to the longitudinal plane of the fuselage. The third engine is arranged in the plane of symmetry of the channel corresponding to the longitudinal plane and is mounted on the upper part of the fuselage in a raised manner and in front of the tail sections, so that the outlet of the third engine is situated substantially at the inlet of the channel defined by the tail sections.

Abstract: A propulsive system for aircraft that has a jet engine and a nacelle surrounding the aforementioned jet engine. The nacelle has a front section fixed relative to the jet engine, and a rear extremity behind the front section, and has a rear section with two petals hinged relative to the front section. Each of the two petals in a position called zero-setting forms an extension of the front section of the nacelle in which the inside and outside surfaces of the petals and, respectively, determine the aerodynamic forms of the rear section, which are in geometric continuity with the inside and outside surfaces and, respectively, that determine the aerodynamic forms of the front section. The petals can be set individually at a positive or negative setting angle to put into play the reverser, APU, air brake, vectorial, and taxiing modes of the propulsive system.