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 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: An aircraft includes a fuselage having a shape elongated along a longitudinal axis X of the aircraft 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 aircraft reference system and substantially rectilinear.

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: An aircraft has a fuselage 1 of elongated form along a longitudinal axis X corresponding essentially to the longitudinal axis of the aircraft. In a first forward section, the fuselage comprises a cockpit 22 in front of a cockpit bulkhead 51 and a front landing gear 4 associated with a landing gear compartment 41 located behind the cockpit bulkhead 51. The front landing gear 4 and its landing gear compartment 41 are preferably at least partially beneath the floorboard of a compartment of the lower space of the fuselage and in a bulge 24 that increases the volume available for installation of the landing gear.

Abstract: The invention relates to a multi-engine aircraft whose at least two engines (2, 3) are fixed to the fuselage wings symmetrically with respect to the longitudinal vertical plane of symmetry thereof, respectively and the third engine (7) is provided for the tail of the fuselage which comprises tail-planes in the view of said longitudinal plane. The tail-planes (9, 10) define a channel (11) symmetrical with respect to the longitudinal plane of the fuselage and the third engine (7) is disposed on the plane of symmetry of the channel corresponding to the longitudinal plane and mounted on the top part of the fuselage in an elevated manner and before the tail-planes in such a way that output of said third engine is arranged substantially upon the input of the channel (11) defined by said tail-planes.

Abstract: A multi-engine aircraft having one engine positioned at the tail of the fuselage may include rear tail units in a vertical longitudinal plane-of-symmetry of the fuselage. The tail engine is disposed in front of the rear tail units on the upper part of the tail of the fuselage. The tail engine is mounted, in a detachable manner, on a rigid supporting structure attached to the supporting structure of the fuselage. A lowering shaft, formed in the tail of the fuselage and plumb with the engine, is supported by the rigid supporting structure. The lowering shaft provides a passage for the engine between a high position corresponding to the operational position of the engine and a low position in which the engine is removed from the fuselage.

Abstract: The present invention relates to a multi-engined aircraft of which one (7) of the engines is positioned at the tail (9) of the fuselage (6), which comprises the rear tail units, and in the vertical longitudinal plane of symmetry of said fuselage. Advantageously, said tail engine (7) is disposed in front of the rear tail units, on the upper part (8) of the tail of the fuselage, and is mounted, in detachable manner, on a rigid supporting structure (15) attached to that of said fuselage and there is formed, in the tail (9) of said fuselage and plumb with said engine (7) supported by said structure (15), a lowering shaft (16) for the passage of said engine between, on the one hand, a high position corresponding to the operational position of said engine and, on the other hand, following the separation of said engine from the supporting structure and its displacement through said lowering shaft, a low position in which said engine has come out of said fuselage (6) and is under said tail.