Abstract: An aircraft has at least two jet-propulsion engines mounted laterally on the fuselage in a symmetrical design in the aft part of the fuselage. Each jet engine is mounted on the fuselage some distance from the vertical plane of symmetry of the aircraft, so that the jet engine, in a so-called half-buried configuration, is partly inside an envelope surface of a theoretical fuselage. The half-buried, jet engines are mounted on a main boom fitted on the vertical plane of symmetry of the aircraft, inside the fuselage in back, of a forward main frame. The tail sections are mounted on the main boom and the boom is integral with structures for transmitting forces into the forward part of the fuselage. The structure is advantageously made of fiber-reinforced composite materials.

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 capable of making short takeoffs and landings includes essentially a fuselage, a wing secured to the fuselage, a front horizontal stabilizer secured to the fuselage on the front end of the fuselage and at least two jet engines for propulsion. According to the architecture proposed, the propulsion engines are arranged side by side above the fuselage in a rear part of the fuselage with a width at least equal to the width of the propulsion group, a fuselage flap device is arranged in the back of the fuselage so that the fuselage flaps adopt at least a position in which the flaps are considerably in a horizontal plane and take at least a high-lift position in which the flaps are turned downward in such a way that the blast created by the jet engines is channeled towards the top surface of the fuselage flaps to induce a blowing effect.

Abstract: A method for aiding modelling 3D objects permits production of a parameterizable instantiate model of a 3D object from a generic model of the object and a specific model of a second object including at least a part of first object. Certain characteristic data are extracted from the specific model of the second 3D object according to the parameters of the generic model of the first 3D object. A parameterizable instantiate model is produced from the generic model of the first 3D model by matching this model to the extracted data.

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: A large-capacity airplane principally includes a fuselage which has no region of constant width between the front and the rear and a wing fixed to the fuselage. As a preference, the engines are fixed at the rear under a horizontal tail held above the fuselage by vertical stabilizers and maintenance wells are formed in the fuselage in vertical alignment with each engine to allow the engines to be fitted and removed. The width of the fuselage is determined, on the one hand, so that the airplane landing gear is fixed to the fuselage and in the up position is included within the interior volume of the fuselage and, on the other hand, so that the rear engines are above the fuselage in order to make use of the beneficial effects of this position.

Abstract: An aircraft has a fuselage a wing integral with the fuselage at a point on a rigid central wing box. Sections of the wing are located on sides of the central wing box and integral and fixed relative to the wing box to form a rigid wing. The wing is mounted movably in translation relative to the fuselage along a longitudinal direction of the aircraft parallel to an axis of the fuselage between an extreme forward position and an extreme rear position of a point of reference of the wing. The central wing box is determined in the front by a wing box front spar, in the rear by a wing box rear spar, and laterally by root ribs. Sections of the wing include external front and external rear spars integral with and fixed relative to the wing box front spars and wing box rear spars to form the rigid wing.

Abstract: An aircraft has a vertical fin fastened to the rear and above a fuselage of elongated form, essentially in a vertical plane of symmetry of the aircraft. The vertical fin has at least two stable positions, an extended position and a returned position, such that a surface of the vertical fin, subjected to an aerodynamic flow when the aircraft is in flight, is modified in position or in surface between the returned position and the extended position, so that the aerodynamic drag of the vertical fin is reduced in the returned position under given flight conditions compared to the extended position. The change from one surface to another of the vertical fin is accomplished by modifying the geometry of the vertical fin or by displacing the vertical fin relative to the fuselage so that the vertical fin, for example, is more or less inside the fuselage, or more or less immersed in the wake zone of the fuselage in which the local dynamic pressure Pd is reduced relative to the infinitely upstream dynamic pressure Pd0.

Abstract: A rear tail assembly for an aircraft, including a fuselage, a wing and at least one propulsion engine attached in the rear portion of the fuselage located behind the wing along the X longitudinal axis of the aircraft, wherein the aforementioned assembly includes aerodynamic surfaces connected in the rear portion of the fuselage. The tail assembly essentially includes horizontal aerodynamic surfaces and essentially vertical aerodynamic surface arranged so as to form an annular structure including at least one ring attached to the fuselage. At lease one engine is held in the ring formed by the tail assembly. In one embodiment, a central fin is used for defining two rings in the annular structure. In particular embodiments of an aircraft including such a tail assembly, one or two engines can be fitted in the ring area.

Abstract: An aircraft includes a reference system including a longitudinal X axis, a vertical Z axis perpendicular to the X axis, and a lateral Y axis perpendicular to the plane defined by the X and Z axes, a fuselage, a wing affixed to an upper central part of the fuselage, a set of rear airfoils situated behind the wing, and propulsion engines mounted on the wing, where the wing, the set of rear airfoils and the propulsion engines are parts of an aero-propulsive unit forming a structure independent of the fuselage, and where the aero-propulsive unit is connected to the fuselage by a six degrees of freedom connection system using arms with lengths modified to control a position of the aero-propulsive unit relative to the fuselage along the X, Y and Z axes and in rotation about the X, Y and Z axes, during flight.

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: A propulsive system for an aircraft including an auxiliary jet engine is integrated into a tail cone of a fuselage. A carrying structure of the jet engine is primarily formed with beams and frames or half-frames to which the auxiliary jet engine is fixed by lateral beams. The beams are interdependent of the frames and half-frames, and the beams are overhanging behind a frame behind which is fixed the engine. Each beam includes a lower half-beam and a higher half-beam, separated on at least a part of its length ahead from attachments of the jet engine to determine a space free of structure impediment for lateral air intakes.

Abstract: A propulsive system for an aircraft including an auxiliary jet engine is integrated within a tail cone of a fuselage. Lateral air intakes include each one a scoop movable between a closed position and an opened position are associated with aerodynamic channels to supply with air the auxiliary jet engine. The aerodynamic channels meet at a common channel including a movable flap to balance air flows coming from the air intakes when the operation is not symmetrical.

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, the propulsive units of which include engines, and which is distinguished by reduced noise emissions, includes a wing structure fixed to an upper region of the fuselage, and a vertical tail system having at least two vertical stabilizers which are generally vertically fixed to the fuselage aftwardly of the wing structure. The engines are disposed side by side in a propulsive package disposed above the fuselage, which propulsive package includes the following: air inlet openings for the propulsive package, which openings are disposed above the fuselage between a point at the leading edge and a point at the trailing edge of an aerodynamic root chord of the wing structure; and exhaust nozzle conduit outlets associated with exhaust nozzle conduits, which outlets are formed by the structure (cowling structure) of the propulsive package, and are disposed above the fuselage forwardly of an aft terminus of the fuselage and between the vertical stabilizers.

Abstract: When an aircraft is propelled by at least one jet engine fixed in a rear part of the aircraft, at least one substantially horizontal rear aerodynamic surface, the rear horizontal surface, is arranged at the rear of the aircraft and at least one jet engine is fixed under the rear horizontal surface by an attachment mast fixed by its upper part to the rear horizontal surface and maintains, by its lower part, the jet engine. The rear horizontal surface is also the horizontal tail unit of the aircraft or a horizontal surface maintained above the fuselage. The rear surfaces and the fuselage are arranged such that the engines are installed and removed using a vertical movement of the engines, which are advantageously one, two or three in number, in the rear zone of the aircraft.

Abstract: To be able to transport and replace in an autonomous manner one of its failing propulsion engines, a plane includes: a fuselage; propulsion engines maintained above the fuselage; maintenance wells traversing the fuselage substantially vertically with respect to the engines in which the engines can be lifted or lowered; a cargo compartment including a floor arranged in the fuselage, where the height, length and width dimensions of the cargo compartment are compatible with the transport of an engine; the cargo compartment and the wells have a common separation wall including an exit whose dimensions allow the passage of an engine; and a lower hatch or ramp for closing the lower opening of the well includes a position in which the upper surface of the ramp is substantially horizontal and substantially in the extension of the floor of the cargo compartment.