| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | TILT WING ROTOR VTOL | EP11770063.3 | 2011-09-16 | EP2616335A1 | 2013-07-24 | Reiter, Johannes |
| The present invention relates to an aircraft (110) for vertical take-off and landing. The aircraft comprises a first wing (101), a second wing (102) and a fuselage (103). The first wing (101) comprises a first longitudinal wing axis (104) and the second wing (102) comprises a second longitudinal wing axis (104). The first wing (101) extends along the first longitudinal wing axis (104) and the second wing (102) extends along the second longitudinal wing axis (104) from the fuselage (103). The first wing (101) is tiltable with a first rotational direction around the first longitudinal wing axis (104) and the second wing (102) is tiltable with a second rotational direction around the second longitudinal wing axis (104). The wings (101, 102) are adapted in such a way that, in a fixed- wing flight mode, the wings (101, 102) do not rotate around a second axis (105). The wings (101, 102) are further adapted in such a way that, in a hover flight mode, the wings (101, 102) are tilted around the longitudinal wing axis (104) with respect to its orientation in the fixed- wing flight mode and that the wing (100) rotates around the second axis (105). | ||||||
| 122 | DRONE MINIATURISE A ATTERISSAGE ET DECOLLAGE VERTICAL | EP05769703.9 | 2005-05-27 | EP1750999B1 | 2012-07-11 | LAVAL-JEANTET, Rémi; TROUCHET, Daniel; BROSSAY, Nicolas; BINETTI, Paolo |
| The invention concerns a vertical take-off and landing miniature drone, comprising a substantially cylindrical annular fairing (10), two counter-rotating propellers (26, 32) mounted rotatably in the fairing about the axis thereof and driven at the same speed, and control surfaces, located between the cylindrical body and the fairing beneath the propellers, which comprise pivoting boxes (34) open at their upper and lower ends and containing profiled blades. | ||||||
| 123 | CONVERTIBLE VERTICAL TAKE-OFF AND LANDING MINIATURE AERIAL VEHICLE | EP03713175.2 | 2003-02-19 | EP1476354B1 | 2008-11-05 | BARRETT, Ronald, Martin |
| A vertical take-off and landing miniature aerial vehicle includes an upper fuselage segment (12) and a lower fuselage segment (14) that extend in opposite directions from a rotor guard assembly (16). A rotor (52) rotates within the rotor guard assembly (16) between the fuselage segments(12, 14). Plural turning vanes (28) extend from the rotor guard assembly (16) beneath the rotor (52). Moreover, plural grid fins (26) extend radially from the lower fuselage segment (14) below the turning vanes (28). The aerial vehicle is capable of taking off and landing vertically. During flight, the aerial vehicle can hover and transition between a horizontal flight mode and a vertical flight mode using the grid fins (26). | ||||||
| 124 | TAILBOOM-STABILIZED VTOL AIRCRAFT | EP04817324.9 | 2004-10-19 | EP1689638A2 | 2006-08-16 | Baldwin, Douglas G. |
| A disclosed flying craft (100) includes a suspension structure (110) having a first end and a second end, a lift unit (150), and a payload unit (190). The lift unit includes a nacelle (128) and a tailboom (140), and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure’s second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed. | ||||||
| 125 | Vtol aircraft | EP03016319.0 | 2003-07-18 | EP1396423A1 | 2004-03-10 | Perlo, Piero; Bollea, Denis; Alacqua, Stefano; Finizio, Roberto; Carvignese, Cosimo; Balocco, Elena |
VTOL aircraft comprising a first and a second ducted rotor (1, 2) positioned at the ends (8, 9) of a vertical fuselage (3) and whose propellers (4, 6) are driven to rotate in mutually opposite directions. Control flaps (13) for orientation and transverse flight are operatively associated at least to the lower ducted rotor (2). |
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| 126 | STABILIZING CONTROL APPARATUS FOR ROBOTIC OR REMOTELY CONTROLLED FLYING PLATFORM | EP99972834.8 | 1999-12-10 | EP1144249B1 | 2003-09-03 | MOLLER, Paul, S. |
| A robotic or remotely controlled flying platform (10) with reduced drag stabilizing control apparatus constructed having an air duct (12) with an air intake (14) on the top and an exhaust (16) at the bottom, containing supported therein a clockwise rotating fan (22) and a counter-clockwise rotating fan (24). Directly below the perimeter of the air duct exhaust are mounted a plurality of trough shaped air deflection assemblies (32) each including a rotatably adjustable half trough (44) for selectively scooping a portion of the drive air, and a stationary adjacent half trough (36) for receiving the scooped drive air and redirecting it outward and upward from the air duct. A centrally positioned plate (112) has a plurality of rods (106), each pivotably connected between the plate (74) and a corresponding lever associated with each of the adjustable half troughs (44) so as to couple the adjustable half trough (44) in or out of the drive air steam according to the position of the plate (74), thereby providing control over the pitch and roll of the flying platform. The plate is driven by first and second motors responding to input control signals. The control signals also direct the yaw of the flying platform by selectively providing independent speed control to each of the clockwise and counter clockwise fan motors resulting in duct rotation in a clockwise or counter clockwise direction accordingly. | ||||||
| 127 | VTOL aircraft with variable wing sweep | EP00127980.1 | 2000-12-20 | EP1114772B1 | 2003-04-16 | Ingram, David Barry |
| An aircraft (10) capable of vertical take off with the fuselage generally vertical and normal cruise flight with the fuselage generally horizontal has a fuselage (12) and a pair of wings (13,14), the wings (13,14) being movable relative to the fuselage (12) from a rearwardly swept position to which the wings (13,14) are moved for vertical take off, to a spread position to which the wings (13,14) are moved for normal cruise flight. | ||||||
| 128 | Amphibious aircraft | EP02021682.6 | 2002-09-27 | EP1298054A2 | 2003-04-02 | Tanaka, Akio |
A sea-land-sky craft capable of navigating on the water, running on the land and flying in the air (that is, climbing vertically, flying horizontally and hovering in the air) usable in a new transportation system. The sea-land-sky craft comprises counter-rotating rotors (14,15). Rotor shafts (12,13) are disposed at positions eccentric to the centers of the rotors and carry the rotors so that the orientation of the rotating wings can be turned. A cylindrical duct encloses the outer circumferences of the maximum diameters of the rotors rotations. A fuselage is located at a central portion of the craft. Movable struts are provided for connecting the cylindrical duct and the fuselage. In the sea-land-sky craft, the cylindrical duct is deformed into a fixed wing by the actions of the movable struts. |
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| 129 | STABILIZING CONTROL APPARATUS FOR ROBOTIC OR REMOTELY CONTROLLED FLYING PLATFORM | EP99972834.8 | 1999-12-10 | EP1144249A2 | 2001-10-17 | MOLLER, Paul, S. |
| A robotic or remotely controlled flying platform (10) with reduced drag stabilizing control apparatus constructed having an air duct (12) with an air intake (14) on the top and an exhaust (16) at the bottom, containing supported therein a clockwise rotating fan (22) and a counter-clockwise rotating fan (24). Directly below the perimeter of the air duct exhaust are mounted a plurality of trough shaped air deflection assemblies (32) each including a rotatably adjustable half trough (44) for selectively scooping a portion of the drive air, and a stationary adjacent half trough (36) for receiving the scooped drive air and redirecting it outward and upward from the air duct. A centrally positioned plate (112) has a plurality of rods (106), each pivotably connected between the plate (74) and a corresponding lever associated with each of the adjustable half troughs (44) so as to couple the adjustable half trough (44) in or out of the drive air steam according to the position of the plate (74), thereby providing control over the pitch and roll of the flying platform. The plate is driven by first and second motors responding to input control signals. The control signals also direct the yaw of the flying platform by selectively providing independent speed control to each of the clockwise and counter clockwise fan motors resulting in duct rotation in a clockwise or counter clockwise direction accordingly. | ||||||
| 130 | STOL/VTOL FREE WING AIRCRAFT WITH ARTICULATED TAIL BOOM | EP94908602.9 | 1994-01-21 | EP0680436B1 | 1998-11-18 | RUTAN, Elbert, L.; SCHMITTLE, Hugh, J. |
| A VTOL/STOL free wing aircraft (100) includes a free wing (110) having wings on opposite sides of a fuselage (102) connected to one another respectively adjacent fixed wing inboard or center root sections (117) fixedly attached to the fuselage (102) for free rotation about a spanwise axis (112). Horizontal and vertical tail surfaces (138, 140) are located at the rear end of a boom assembly (120) rotatably connected to the fuselage (102). A gearing (150) or screw rod (160) arrangement controlled by the pilot or remote control operator selectively relatively pivots the fuselage (102) in relation to the tail boom assembly (120) to enable the fuselage to assume a tilted or nose up configuration to enable VTOL/STOL flight. | ||||||
| 131 | LOCKABLE FREE WING AIRCRAFT. | EP92925289 | 1992-11-20 | EP0621843A4 | 1995-07-12 | SCHMITTLE HUGH J |
| 132 | An unmanned vertical take-off and landing, horizontal cruise, air vehicle | EP93310646.0 | 1993-12-31 | EP0661206A1 | 1995-07-05 | Ebbert, Marvin D.; Gustin, Russell G.; Horbett, Edward C.; Edwards, Jack J.; Adcock, Clifton L. |
An unmanned air vehicle capable of vertical take-off and landing, hovering and high-speed horizontal cruise flight. A forward centerbody (16) houses an engine (26) and carries a single rotor assembly (34) having a plurality of propellers (38) lying in a plane substantially perpendicular to the centerline of the forward centerbody (16). A coaxial aft centerbody (18) is secured to the aft end of the forward centerbody (16) and typically houses the vehicle avionics. A plurality of stators (44) extend outwardly of the aft centerbody (18), in a plane substantially parallel to the propellers (38). A single toroidal duct (12) surrounds the rotor assembly (34) and the stators (44) and is secured to the stators (44). A plurality of movable control vanes (52) are secured between the duct (12) and aft centerbody (18) aft of the stators (44). A flight control system, typically housed in the aft centerbody (18), controls the engine (26) and the vanes (52) to cause the vehicle to selectively move upwardly, downwardly, hover or translate to forward, horizontal, motion with the rotor in a plane within 80° of vertical. A sensor, cargo, or other payload may be carried at the forward end (14) of the forward centerbody (16), extending well in front of the duct (12). The vehicle is highly maneuverable, light weight and safe for operation from a small area due to the ducted rotor. |
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| 133 | THRUST VECTORING FREE WING AIRCRAFT | EP93907455.0 | 1993-03-12 | EP0629164A1 | 1994-12-21 | SCHMITTLE, Hugh J. |
| Un aéronef à décollage et à atterrissage verticaux (10) comprend une aile libre (16) constituée d'ailes situées sur les côtés opposés du fuselage (12) et interconnectées de manière à pouvoir tourner librement sans joints, dont le pas différentiel peut être ajusté par le pilote, par un ordinateur ou par télécommande. Pendant le lancement vertical, les gouvernes de profondeur (26) et de direction (24), ainsi que le réglage du pas différentiel des ailes commandent la profondeur, le lacet et le roulis, respectivement. Pendant le lancement, la gouverne de profondeur (26) incline le nez du fuselage (12) vers le bas afin de modifier le vecteur de poussée et accélérer horizontalement l'aéronef, alors que l'aile libre (16) tourne par rapport au fuselage (12) jusqu'à une position généralement horizontale afin de porter l'aéronef pendant le vol horizontal. La transition du vol horizontal au vol vertical est obtenue par le procédé inverse et l'aéronef peut être doucement récupéré dans ou sur une surface élastique telle qu'un filet (66). | ||||||
| 134 | MULTIFUNCTIONAL FLYING VEHICLE. | EP93916330 | 1993-07-08 | EP0601212A4 | 1994-11-30 | DEMIDOV GERMAN VIKTOROVICH; OSIPOV EDUARD SERAFIMOVICH |
| The invention relates to the aviation industry and concerns means for transportation of liquid and bulk loads. The aim of the invention consists in creating a flying vehicle capable of lifting a multi-ton load from a limited site. The aim is achieved due to the fact that in a flying vehicle the carrying aerodynamic structure consists of two parts: an immobile part in the form of a fuselage-ring (1) consisting, in turn, of aerodynamic spanwise curved elements (2, 3), and a movable part in the form of carrying rotor units (6) located along the perimeter of the ring. The engine installation comprises a gas generator, propulsive units, ramjet contours and flywheel elements interconnected through a reversible injecting engine (22) of rotor-piston type and a hydraulic torque converter. | ||||||
| 135 | TRANSPORTATION SYSTEM AND METHOD FOR POD ASSEMBLY SELECTIVELY ATTACHABLE TO AIRCRAFT | EP18186939.7 | 2016-08-25 | EP3418187A1 | 2018-12-26 | McCULLOUGH, John Richard; OLDROYD, Paul K. |
The present disclosure relates to a transportation system and services method including receiving, at a transportation services provider system, a request for transportation of a pod assembly (170) having a current location and a destination; uploading a flight plan to a flight control system of a flying frame (112) including an airframe and a propulsion system; dispatching the flying frame (112) to the current location of the pod assembly (170); coupling the flying frame (112) to the pod assembly (170) at the current location of the pod assembly (170); transporting the pod assembly (170) by air from the current location of the pod assembly (170) to the destination of the pod assembly (170); and decoupling the pod assembly (170) from the flying frame (112) at the destination of the pod assembly (170).
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| 136 | HIGH-AUTHORITY YAW CONTROL FOR A TANDEM VEHICLE WITH RIGID ROTORS | EP15858679 | 2015-11-10 | EP3218261A4 | 2018-07-18 | HEIN BENJAMIN REED |
| A method for executing yaw control of an aircraft including two rotors is provided. The method includes inducing helicopter yaw by creating a differential torque between the two rotors, wherein the creating of the differential torque comprises inducing a differential collective pitch to generate a differential thrust, and maintaining helicopter roll equilibrium during the inducing of the helicopter yaw by inducing a differential cyclic pitch to generate a differential lift offset. | ||||||
| 137 | CONTROL OF AN UNMANNED AERIAL VEHICLE | EP12835896.7 | 2012-09-14 | EP2760739B1 | 2017-11-22 | CHAN, Keen Ian |
| An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method for assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises a wing structure comprising elongated equal first and second wings; a support structure comprising first and second sections coupled to a middle position of the wing structure and extending in opposite directions perpendicular to the wing structure; and four propellers, each mounted to a respective one of the first and second wings, and first and second sections, for powering the UAV during both vertical and horizontal flight modes. | ||||||
| 138 | FORWARD FOLDING ROTOR BLADES | EP17170906.6 | 2017-05-12 | EP3243745A1 | 2017-11-15 | FENNY, Carlos Alexander; OLSON, Rohn Lee; ZAHASKY, Andrew James |
An aircraft (100) comprising a plurality of engines (132) including two or more rotor blades (202), each rotor blade (202) in mechanical communication with a hub (304) and pivotable about an axis of rotation, a bearing plate (308) comprising a rotating portion (308a) and a non-rotating portion (308b), a fold linkage (306) coupled to the rotating portion (308a) of the bearing plate (308) and in mechanical communication with the rotor blade (202), and an actuator (310) coupled to the non-rotating portion (308b) of the bearing plate (308) and operable to reposition the bearing plate (308) from a first position (312) to a second position (314) such that the folding links (306) pivot the rotor blades (202) from a deployed position to a forward folded position.
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| 139 | HIGH SPEED MULTI-ROTOR VERTICAL TAKEOFF AND LANDING AIRCRAFT | EP15862818.0 | 2015-10-28 | EP3224140A1 | 2017-10-04 | CLARIDGE, Jerry, Daniel; MANNING, Charles, Fischer |
| This disclosure is generally directed to a High Speed vertical takeoff and landing (VTOL) aircraft that includes fixed wing flight capabilities. The High Speed VTOL aircraft may include at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a main wing, and at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a vertical wing. The rotors may be driven by electric motors. However, other power sources may be used such as combustion or hybrid engines. By adjusting the speed and/or the pitch of the rotors, the aircraft can transition from a vertical flight configuration to a horizontal flight configuration and back. | ||||||
| 140 | AN UNMANNED AERIAL VEHICLE | EP13900333 | 2013-12-24 | EP3087003A4 | 2017-09-13 | CHAN KEEN IAN |
| An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method of assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point; a connecting structure extending substantially perpendicularly from the elongated wing structure, the connecting structure being offset from the middle location of the elongated wing structure at a first position along the elongated axis; and at least three sets of propellers, wherein at least two sets of propellers are mounted on the connecting structure, and wherein at least one set of propellers is mounted at a second position offset from the middle location in an opposite direction away from the connecting structure. | ||||||
