Class / Patent application number | Description | Number of patent applications / Date published |
244055000 | Arrangement | 15 |
20080258005 | Aircraft Having a Reduced Environmental Impact - Disclosed is an aircraft having a reduced environmental impact. According to the invention, this aircraft comprises at least one engine ( | 10-23-2008 |
20080265088 | Propulsion System for Model Airplane - An improved structure and method for powering the flight of a model airplane by positioning the motors and propellers on the back side of the top wings of an airplane using a single or double-deck wing design so that the propellers and motors of the airplane are better protected from damage in the event of a crash. The fuselage of the airplane is formed of a deformable material such as a foam to aid in crash resistance. | 10-30-2008 |
20090140096 | Impact resistant aircraft fuselage - The invention relates to a structural configuration of the rear fuselage ( | 06-04-2009 |
20100032518 | AIRCRAFT FUSELAGE - An aircraft fuselage including a front part including a cockpit, a central part, and a rear part. The central part of the fuselage includes a first zone located at the front part and that increases in width to a maximum width towards the rear of the aircraft, a second zone that decreases in width, and a third zone that has an essentially constant width and is located behind the second zone, width begin measured along the pitch axis. | 02-11-2010 |
20100133377 | AIRPLANE WITH FLAT REAR FUSELAGE SAID QUEUE-DE-MORUE EMPENNAGE - 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. | 06-03-2010 |
20100155526 | AIRCRAFT WITH TAIL PROPELLER-ENGINE LAYOUT - An aircraft propeller-engine layout includes at least one engine ( | 06-24-2010 |
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 |
20130062463 | TRANSVERSE MOUNTED GAS TURBINE ENGINE - A propulsion engine comprises a compressor, a combustor and a turbine arranged in flow series about a turbine axis. A shaft is coupled to the turbine along the turbine axis, and first and second propulsions fans are rotationally coupled to the turbine at opposite ends of the shaft. The first and second propulsion fans rotate substantially parallel to one another, and transversely with respect to the turbine axis. | 03-14-2013 |
20130214090 | AIRCRAFT WITH FUSELAGE-MOUNTED ENGINES AND AN INTERNAL SHIELD - Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield. | 08-22-2013 |
20140145027 | AIRCRAFT WITH AN INTEGRAL AERODYNAMIC CONFIGURATION - The invention relates to multimode aircraft operated at supersonic and subsonic flight speeds in a wide range of flight altitudes. The invention is particularly applicable in multimode super-maneuverable aircraft capable of cruising at supersonic speed and having low radar signature. The technical effect to be achieved by the invention is to provide an aircraft which has low radar signature, is super-maneuverable at high angles of attack, has high aerodynamic efficiency at supersonic speeds while keeping high aerodynamic efficiency at subsonic modes, and can accommodate bulky cargo in its internal compartments. The integral aerodynamic configuration aircraft comprises fuselage ( | 05-29-2014 |
20140252160 | REVERSE FLOW GAS TURBINE ENGINE REMOVABLE CORE - An engine mounting arrangement includes a propulsor mounted to an aircraft wing, and an engine core aerodynamically connected to the propulsor and positioned rearward of the propulsor. | 09-11-2014 |
20150307198 | ASSEMBLY FOR AN AIRCRAFT COMPRISING A MOVEABLE ACCESS PANEL - An assembly for an aircraft with an engine includes an attachment device intended to support the engine, a pod intended to surround the engine and including a cover, joints intended to allow articulation of the cover and allow movement of the cover relative to the attachment device between a closed position and an open position, and at least one access panel mounted moveably on the cover between a closed position, in which the access panel extends continuously between the cover and the attachment device when the cover is in the closed position, and an open position in which the access panel is remote from its closed position. The assembly includes a handle which can be operated from the outside of the cover between a first position and a second position, and a transmission system provided to move said or each access panel from its closed position to its open position. | 10-29-2015 |
244056000 | Tilting | 3 |
20090159741 | Optimized configuration of engines for aircraft - The invention relates to a configuration of engines ( | 06-25-2009 |
20100019081 | AIRPLANE WITH PITCH AND YAW COMMAND BY PROPULSION SYSTEM - Swiveling engines | 01-28-2010 |
20130153708 | AFT-LOADING AIRCRAFT WITH TWIN T-TAIL ASSEMBLY - An aft-loading aircraft with a twin T-tail assembly is provided. In one example embodiment, the aft-loading aircraft includes a fuselage portion having an aft opening with a cargo door, a first and second vertical stabilizer attached to the fuselage portion, and, a horizontal stabilizer transversely attached to the first and second vertical stabilizers. | 06-20-2013 |