| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | Aircraft | US3576300D | 1969-07-23 | US3576300A | 1971-04-27 | PALFREYMAN JACK |
| An aircraft with good noise characteristics has a number of rear-mounted engines which are arranged to suck boundary layer air from the top of the fuselage to convert the latter in its entirety to a lifting body. The tail of the aircraft acts as a noise shield.
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| 162 | High-speed flight vehicle control | US3570789D | 1969-06-30 | US3570789A | 1971-03-16 | RAINEY ROBERT W |
| A vehicle having supersonic and hypersonic flight capabilities equipped with a pair of elevons on the aft end of the body and disposed with hinge lines swept forward relative to the aircraft centerline at an angle less than 90*.
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| 163 | Tandem Wing Aircraft With Variable Lift And Enhanced Safety | US15933012 | 2018-03-22 | US20180222584A1 | 2018-08-09 | Robert N. Dunn; Lawrence R. Dunn |
| A tandem wing aircraft having a fore wing, an aft wing, and a middle wing, attached relative to the aircraft and each other such that the middle wing provides a substantial portion of the total lift at landing speeds, and a minimal portion of the total lift at cruise speeds. At cruise speeds, induced drag is minimized, permitting higher speeds, greater fuel efficiency, and/or greater payload. Advantageously, the wing loading at cruise speeds is higher providing better passenger comfort while still providing controllability and safety at landing speeds. | ||||||
| 164 | LIFT GENERATING FUSELAGE FOR AIRCRAFT | US15746444 | 2016-07-26 | US20180170508A1 | 2018-06-21 | Rajan J BHATT |
| The present lift generating fuselage (1) for aircraft mainly comprises of: a novel aerofoil shaped fuselage (1A); or a novel aerofoil shaped fuselage body (2); and integral webs (3); or a novel aerofoil shaped fuselage body (2); integral webs (3) and overhead central wing (4). | ||||||
| 165 | AIRCRAFT HAVING SUPPORTING FUSELAGE | US15557347 | 2016-03-09 | US20180105255A1 | 2018-04-19 | Roberto Horacio Blanco; Alejandro José Klarenberg; Carlos Conrado Bosio Blanco |
| The aircraft defines a lifting volume including at least part of the central body housing the transported payload. Said volume has a conventional aerodynamic profile along the longitudinal direction of the aircraft, with portions of wings projecting symmetrically and transversely at both sides thereof. From the longitudinal axis said wings at each side shows corresponding first sections with negative dihedral and forward swept until reaching corresponding inflexion points from which two distal second sections or tracts projects with positive dihedral and back swept until reaching the wingtips of the projected wingspan. | ||||||
| 166 | Aircraft | US14976414 | 2015-12-21 | US09815559B2 | 2017-11-14 | Matthew Moxon |
| An aircraft (2) comprises at least first and second gas turbine engines (10a, 10b) arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine (10a, 10b) comprising at least one compressor or turbine rotor disc (32-42) defining a respective rotational plane (D32-D42). The rotational plane (D32-D42) of at least one of the rotors (32-42) of at least one of the engines (10a, 10b) is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine (10a, 10b) is nonintersecting with another engine (10a, 10b). | ||||||
| 167 | Propulsion system for an aerial vehicle | US14899636 | 2014-06-25 | US09789959B2 | 2017-10-17 | Erik Prisell |
| The invention relates to a propulsion system concept that is a propulsion system that is integrated in the hull of an aerial vehicle (1), which propulsion concept comprises at least one differential velocity fan (4), which is arranged on a shaft driven by one or more power units (2). The propulsion concept is intended to provide short takeoff and landing distances, high flight speed (high subsonic to transsonic) and to be able to provide low IR signature, low radar signature, a small cross section and low air resistance. The propulsion concept is called HPVO (High Performance Optimized Versatile propulsion). The invention is useful both for air vehicles of the type for conventional takeoff and landing, “CTOL” (Conventional Take Off and Landing), “Chair” and for vertical takeoff and landing, “V (t) OL” (Vertical (Take) Off and Landing’) and the flying wing (blended-body). The concept is applicable to both large and small aircraft, manned as well as unmanned aerial vehicles. | ||||||
| 168 | DOORS FOR AN EASY ACCESS TO THE PRESSURIZED HOUSING OF A FLYING WING, FROM THE TRAILING EDGE | US15441510 | 2017-02-24 | US20170247100A1 | 2017-08-31 | Olivier Cazals; Jaime GENTY DE LA SAGNE |
| 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. | ||||||
| 169 | DOOR OF A BLENDED BODY AIRCRAFT INSTALLED IN THE LEADING EDGE AND WITH LATERAL EDGES PARALLEL TO THE PLANE OF SYMMETRY OF THE AIRCRAFT | US15388836 | 2016-12-22 | US20170183078A1 | 2017-06-29 | Olivier CAZALS; Jaime GENTY DE LA SAGNE |
| 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. | ||||||
| 170 | OBLIQUE BLENDED WING BODY AIRCRAFT | US15232510 | 2016-08-09 | US20170158309A1 | 2017-06-08 | William Randall McDonnell |
| An oblique wing aircraft designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment and an aft swept wing segment. A center oblique airfoil section connects the forward and aft swept wing segments. The center oblique airfoil section has a larger chord near its centerline than the chords of either of the forward or aft swept wing segments. The chord of the center oblique airfoil section tapers down more rapidly than the forward or aft wing segments as the center oblique airfoil section extends outboard toward the forward and aft swept wings. Preferably, the aircraft is an all-wing aircraft. | ||||||
| 171 | Aircraft including a passenger cabin extending around a space defined outside the cabin and inside the aircraft | US14263376 | 2014-04-28 | US09611039B2 | 2017-04-04 | Patrick Lieven; Romain Delahaye; Catalin Perju |
| The sealed bottoms of aircraft passenger cabin have to be fastened with heavily sized fasteners so as to withstand loads induced by the cabin pressurization. Besides, the increase in aircrafts seating capacity makes an increase in passenger cabin widths of interest. Such a width increase however makes the structure delimiting passenger cabin less resistant to efforts induced by the cabin pressurization. The present invention proposes an aircraft wherein the structure delimiting passenger cabin extends over 360 degrees around a space defined outside structure. The invention allows structure to be more resistant to loads induced by the cabin pressurization, while allowing to reduce or even to avoid the need for a sealed bottom, and while allowing to increase the space available for passengers. | ||||||
| 172 | PROPELLER HAVING EXTENDING OUTER BLADE | US14810109 | 2015-07-27 | US20170029091A1 | 2017-02-02 | JONATHON J. LINCH; KYLE M. RAHRIG |
| A propeller includes a hub coaxially surrounding a longitudinal axis. A ring shroud coaxially surrounds the longitudinal axis and is spaced radially from the hub. The ring shroud includes an inner ring surface and a radially spaced, oppositely facing outer ring surface. At least one propeller blade is fixedly attached to both the hub and the inner ring surface and extends radially therebetween for mutual rotation therewith. At least one extending blade has a first extending blade end radially spaced from a second extending blade end. The first extending blade end is fixedly attached to the outer ring surface. The second extending blade end is cantilevered from the first extending blade end and is radially spaced from the ring shroud. | ||||||
| 173 | Oblique blended wing body aircraft | US13784438 | 2013-03-04 | US09440740B2 | 2016-09-13 | William Randall McDonnell |
| An oblique wing aircraft designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment and an aft swept wing segment. A center oblique airfoil section connects the forward and aft swept wing segments. The center oblique airfoil section has a larger chord near its centerline than the chords of either of the forward or aft swept wing segments. The chord of the center oblique airfoil section tapers down more rapidly than the forward or aft wing segments as the center oblique airfoil section extends outboard toward the forward and aft swept wings. Preferably, the aircraft is an all-wing aircraft. | ||||||
| 174 | PROPELLER | US14560964 | 2014-12-04 | US20160159458A1 | 2016-06-09 | JONATHON J. LINCH; Kyle M. Rahrig |
| A propeller includes a hub coaxially surrounding a longitudinal axis. A ring shroud coaxially surrounds the longitudinal axis and is spaced radially from the hub. At least one propeller blade is fixedly attached to both the hub and ring shroud and extends radially therebetween for mutual rotation therewith. At least one stub blade has a first stub end radially spaced from a second stub end. The first stub end is fixedly attached to a selected one of the hub and ring shroud. The second stub end is cantilevered from the first stub end and is radially interposed between the first stub end and the selected one of the hub and ring shroud. | ||||||
| 175 | PROPULSION SYSTEM FOR AN AERIAL VEHICLE | US14899636 | 2014-06-25 | US20160152334A1 | 2016-06-02 | Erik PRISELL |
| The invention relates to a propulsion system concept that is a propulsion system that is integrated in the hull of an aerial vehicle (1), which propulsion concept comprises at least one differential velocity fan (4), which is arranged on a shaft driven by one or more power units (2). The propulsion concept is intended to provide short takeoff and landing distances, high flight speed (high subsonic to transsonic) and to be able to provide low IR signature, low radar signature, a small cross section and low air resistance. The propulsion concept is called HPVO (High Performance Optimized Versatile propulsion). The invention is useful both for air vehicles of the type for conventional takeoff and landing, “CTOL” (Conventional Take Off and Landing), “Chair” and for vertical takeoff and landing, “V (t) OL” (Vertical (Take) Off and Landing’) and the flying wing (blended-body). The concept is applicable to both large and small aircraft, manned as well as unmanned aerial vehicles. | ||||||
| 176 | EMBEDDED ENGINES IN HYBRID BLENDED WING BODY | US14203735 | 2014-03-11 | US20160122005A1 | 2016-05-05 | Razvan Virgil Florea; William T. Cousins; Thomas G. Tillman; David J. Arend; John D. Wolter |
| A hybrid wing aircraft has an engine embedded into a body of the hybrid wing aircraft. The embedded engine has a fan that is received within a nacelle. The body of the aircraft provides a boundary layer over a circumferential portion of a fan. A system delivers additional air to correct fan stability issues raised by the boundary layer. | ||||||
| 177 | Multi-Role Aircraft With Interchangeable Mission Modules | US14951358 | 2015-11-24 | US20160075423A1 | 2016-03-17 | Abe Karem |
| A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that transfer loads across the center section, while accommodating a mid-wing configuration. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft. | ||||||
| 178 | GAS TURBINE ENGINE INLET WALL DESIGN | US14665081 | 2015-03-23 | US20150321764A1 | 2015-11-12 | Dmytro Mykolayovych Voytovych; Om P. Sharma |
| A gas turbine engine includes an inlet duct that is formed with a generally elliptical shape. The inlet duct includes a vertical centerline and a fan section that has an axis of rotation. The axis of rotation is spaced from the vertical centerline and is disposed within an inlet duct orifice. | ||||||
| 179 | REMOTELY OR AUTONOMOUSLY PILOTED REDUCED SIZE AIRCRAFT WITH VERTICAL TAKE-OFF AND LANDING CAPABILITIES | US14054080 | 2013-10-15 | US20150225079A1 | 2015-08-13 | Douglas L. Starck; Errica M. Starck |
| An aircraft having a vertical take-off and landing (“VTOL”) propulsion system aircraft, smaller than a standard manned aircraft and remotely or autonomously piloted. The aircraft comprises a symmetrical airfoil shape for the center body section that consists of ribs and spars maintaining an open area in the center. Situated within the open area of the center of the aircraft resides a duct system consisting of a ducted fan and five outlet vents. The main outlet vent functions as the exhaust exiting the aft portion of the aircraft, with the remaining four ducts used for the VTOL capabilities exiting the underside of the aircraft. The aircraft can have a range of wingspan, which can be scaled to satisfy needs and requirements, with a blended wing body that incorporates the inlet and duct system. | ||||||
| 180 | SOLAR RELAY AIRCRAFT POWERED BY GROUND BASED SOLAR CONCENTRATOR MIRRORS IN DUAL USE WITH POWER TOWERS | US14014261 | 2013-08-29 | US20150021442A1 | 2015-01-22 | John William Hunter |
| A solar relay aircraft system includes a solar relay aircraft having an upper surface, and a lower surface, and equipped with a solar radiation receiver on said lower surface and capable of converting solar energy to electrical energy. An electric motor in electrical connection with said solar radiation receiver to receive the electrical energy and drives a propeller to propel the solar relay aircraft. A number of ground-based reflector arrays include a plurality of reflecting mirrors for receiving solar radiation from the sun and direct the solar radiation from the sun towards the solar relay aircraft. | ||||||
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