Patent application number | Description | Published |
20100019081 | AIRPLANE WITH PITCH AND YAW COMMAND BY PROPULSION SYSTEM - Swiveling engines | 01-28-2010 |
20100032519 | AIRPLANE WITH A MODIFIABLE SURFACE OF VERTICAL EMPANNAGE - 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. | 02-11-2010 |
20100059623 | Aircraft with its fuselage suspended under the wing - An aircraft displaying a fuselage, a wing attached to the fuselage in an upper part and in a middle part along the length of the fuselage, a set of airfoils situated behind the wing and propulsion engines mounted on the wing. The wing, the set of airfoils and the propulsion engines are solidly fastened to an air propulsion unit that is affixed to the fuselage by a connection system permitting the controlled modification in flight of the position of the air propulsion unit relative to the fuselage in the three directions X, Y and Z of the reference aircraft and in rotation around the three directions X, Y and Z. The control of the relative movements of the air propulsion unit and fuselage permits an improved behavior in flight of the airplane and has advantages in the fabrication and operation of the plane. | 03-11-2010 |
20110024556 | Aircraft with yaw control by differential drag - An aircraft having an elongated fuselage and a lifting surface fastened to the fuselage. The aircraft has a device for controlling the torque around the yaw axis GZ of the aircraft in which aerodynamic forms that have devices to generate aerodynamic drag are fastened to each end of the lifting surface at non-zero distances from each side of a vertical plane of symmetry XZ of the aircraft. The drag-generating devices are commanded to produce a different aerodynamic drag at each of the two ends to generate a yaw torque on the aircraft. The aerodynamic forms, for example, have winglets improving the aerodynamics of the lifting surface, and provided with aerodynamic drag generators. | 02-03-2011 |
20110036941 | Aircraft with a wing movable along the longitudinal axis of th fuselage - The aircraft has a fuselage, a wing integral with the fuselage in a middle section in a longitudinal direction of the fuselage, and a tail assembly integral with the fuselage. The wing has a rigid central chamber at the fuselage determined in front by a front spar, in the rear by a rear spar, and laterally by root ribs of the wing. The wing is mounted to be movable longitudinally in translation relative to the fuselage between an extreme forward position Xav and an extreme rearward position Xar so that the center of gravity of the aircraft can be displaced longitudinally to be positioned precisely at any time relative to the point of application of the resultant of the aerodynamic lift forces. The wing is mounted to be movable relative to the fuselage through the intermediary of at least two parallel beams, parallel to the longitudinal axis of the fuselage and integral with the fuselage at the rear/forward bulkhead of the fuselage located on each side of the rigid central chamber. | 02-17-2011 |
20110135472 | AERODYNAMIC FLIGHT CONTROL SURFACE SAID OF CROCODILE STYLE FOR AIRCRAFT - A trailing edge aerodynamic airfoil of a load-bearing aerodynamic surface of an aircraft of the crocodile type has two airfoil flaps, with each flap being integral in a forward section with a rotational shaft that determines the axis of rotation of the airfoil flap. In a position called the zero setting, the airfoil flaps are essentially joined and form a rear section of the load-bearing surface, and each airfoil flap is movable in translation independently of the other airfoil flap, relative to the load-bearing surface, with each flap being entrained in rotation relative to the load-bearing surface around its axis of rotation by the motion in translation. The ends of the rotational shaft have extensions guided by runners fastened to these ends and acting conjointly with racks fastened to the load-bearing surface. | 06-09-2011 |
20110220758 | ARCHITECTURE D'AVION A FUSELAGE LARGE - 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 using conventional means. 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. | 09-15-2011 |
20120325958 | AIRCRAFT WITH REAR ANNULAR TAIL - 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. | 12-27-2012 |