| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | Circular wing | JP2129479 | 1979-02-23 | JPS551266A | 1980-01-08 | HARORUDO JIEIMUSU UOOKAA |
| 22 | "AIR WHEEL" ROTOR. GYRO-STABILIZED AIRCRAFT AND WIND-ENERGY INSTALLATION UTILIZING "AIR WHEEL" ROTOR, AND GROUND-BASED OR SHIP-BASED DEVICE FOR LAUNCHING SAME | EP14900825 | 2014-08-26 | EP3192738A4 | 2018-03-28 | KUZIKOV SERGEJ YUREVICH |
| The group of inventions relates to aviation and wind energy, and specifically to designs of aircraft rotors and cruise propellers. An "Air Wheel" rotor, having blades with variable pitch and variable torsion, contains a closed wing which is connected to one or a plurality of coaxial bushings by means of torsionally-flexible blades, wherein the connection between the blades and the closed wing may be rigid, elastic or viscoelastic. A movable mounting of blades to the one or plurality of bushings is carried out by means of a torsion element, or by means of an axial hinge or by means of an offset axial hinge. The rotor contains a device for controlling the overall/cyclical pitch of the blades, which are set partially or fully by the relative positions (pan, tilt, shift) of the bushings. The blades may have a complex three-dimensional shape. The profile of the torsionally flexible blades may have a variable concavity. A variable torsional rigidity along a blade and/or a transverse bend allow for a hyperbolic blade rotation which maximally approximates the ideal blade rotation. The "air wheel" rotor has a wide range of applications. Design constraints for increasing flight speed are reduced. The efficiency, strength and durability of variable-pitch propellers are increased, losses and noise are decreased, and vibration is eliminated. | ||||||
| 23 | An aircraft of compact dimensions | EP05425074.1 | 2005-02-15 | EP1690788A1 | 2006-08-16 | Perlo, Pietro; Bollea, Denis |
The aircraft (10) comprises a fuselage (12), a main wing (16) substantially of disc-like shape positioned above the fuselage (12), and a secondary wing (18) which intersects the fuselage (12) and is provided with movable control parts. The aircraft further comprises a main propulsion system including an internal combustion engine intended to drive a propeller (26) positioned at the rear of the fuselage (12) and a secondary propulsion system for the propulsion of the aircraft in a direction perpendicular to the ground. The secondary propulsion system includes a matrix of nozzles (32) positioned on the lower surface of the secondary wing (18) and arranged to emit the exhaust gases coming from the main engine in the form of micro-jets. The main propeller propulsion system and the secondary nozzle propulsion system are selectively controllable in such a way that the aircraft is able to perform three different take-off modes, that is to say a first, conventional take-off mode in which only the main propulsion system is used, a second (STOL) take-off mode in which both the main propulsion system and the secondary propulsion system are used, and a third (VTOL) take-off mode in which only the secondary propulsion system is used.
|
||||||
| 24 | CIRCULAR VERTICAL TAKE-OFF AND LANDING AIRCRAFT | EP02703709.2 | 2002-02-26 | EP1370460A1 | 2003-12-17 | Walmsley, Eric Ronald |
| A circular VTOL aircraft with a central vertically mounted turboprop engine (14), driving contra-rotating co-axial propellers (24), above a central jet engine, or engines (12), horizontally mounted on a turntable (11) and steerable through 360 degrees. The turboprop provides vertical thrust from propellers compressing air from an upper circular intake (5) downward through a circular funnel-shaped rotor-chamber (6), to a circular vent (10) at the base of the aircraft. The resulting column of compressed air gives lift for VTOL operations and a cushion of air in flight. The horizontally mounted turbine provides acceleration, retro-thrust and directional control for horizontal flight and vectored thrust for VTOL. An alternative engine configuration (Figure 9), replaces the turboprop and propellers with a vertical turbojet or rocket-engine system providing direct vertical thrust via four control vents (12/14), with an optional horizontal vectored thrust vent (15/37). he aircraft. Fuel-tanks are installed around the central engines. The flight-deck is at the top-centre of the craft above the engines, which are detachable for maintenance. | ||||||
| 25 | A DEVICE FOR GENERATING AN AERODYNAMIC FORCE BY ROTATIONAL MOVEMENT | EP98946175.1 | 1998-09-30 | EP1019284A1 | 2000-07-19 | Bittencourt Sampaio, Eduardo |
| A generator of aerodynamic force by rotational movement, by means of a device which, starting from a rotational movement, induces a field of velocities in the surrounding fluid, which produces a difference in pressure on a surface, which in turn results in an aerodynamic force (if the fluid is air). This aerodynamic force can be used, for instance, to lift heavier-than-air bodies, consuming less power than that required in the devices used at present. The rotor element (1) is set in rotation at high speed by a driving force supplied by a motor (3). The rotational movement of the rotor element (1) causes the fluid in which the device is immersed to assume a rotational movement, the velocity of the fluid layer which is in contact with the cylinder being equal to the velocity of a point at the surface of the cylinder. In addition, the velocity of any particle of the fluid has a direction perpendicular to the radial, and the greater the distance to the centre the lower this velocity is. The planar element (2) separates the fluid into two regions, so that the movement of the fluid in the region above the surface will not induce, in the fluid in the region below the surface, a movement with similar characteristics. Thus, the fluid in the region below the surface can be considered to be motionless, whereas that in the region above the surface is in motion. Since the higher the velocity of the fluid the lower its pressure, it follows that the fluid in the region below the surface exerts, on the latter, a pressure higher than that exerted by the fluid in the region above the surface. This difference in pressure results in a force which acts on the surface. The form of the planar surface (2) has no significant influence on the performance of the device. | ||||||
| 26 | Fluggerät | EP92122020.8 | 1992-12-25 | EP0553490B1 | 1997-04-23 | Bucher, Franz |
| 27 | An aerobatic airplane | EP93108788.6 | 1993-06-01 | EP0574766A1 | 1993-12-22 | Abdurachmanovich, Muchamedov Fatidin |
The invention belongs to aeronautical engineering sphere and can be used in the design of aerobatic airplanes, fighter airplanes. The technical results provided by the realization of a given invention are the following: the increase of the wing lift force at the sacrifice of incorporation of the center - section wing in the process of the lift force forming, and an airplane weight reduction at the sacrifice of more rational structural solution of the problem of loads transfer and their distribution from the outer wing panels to the fuselage. An airplane has the fuselage 1 and the wing, containing the center-section wing 2 and the outer wing panels 3.The tail unit consists of the tailplane 5 and the fins 6. The center-section wing 2 is designed in a disk form with leading 9 and trailing 10 edges along the disk generating line in plan. The engines 7 air intake ducts 11 are designed within the center-section wing 2 disk, and their inlet systems 12 are equiped by the controllable flaps 13, maintaining their complete or partial opening and closing to control an airplane focus position. |
||||||
| 28 | Vertical take-off and landing (VTOL) aerial vehicle and method of operating such a VTOL aerial vehicle | EP12400050.6 | 2012-11-30 | EP2738091B1 | 2015-07-22 | Cvrlje, Tomislav |
| 29 | Vertical take-off and landing (VTOL) aerial vehicle and method of operating such a VTOL aerial vehicle | EP12400050.6 | 2012-11-30 | EP2738091A1 | 2014-06-04 | Cvrlje, Tomislav |
The invention relates to a Vertical Take-off and Landing (VTOL) aerial vehicle (1, 46), e. g. a rotorcraft with long range and high cruising speed capability. The aerial vehicle (1, 46) has a torus-type fuselage (2)with radial inside a duct (5) and at least one main rotor (13, 26). A pair of lateral wings (40) are attached opposed to each other outside the fuselage (2) and at least one engine (18) drives said at least one main rotor (13, 26) and at least two propulsion means (24) fitted to each of said wings (40). The invention relates as well to a method of operating such a VTOL aerial vehicle (1, 46).
|
||||||
| 30 | VEHICLE WITH AERODYNAMIC MODULE | EP96902019 | 1996-01-25 | EP0760338A4 | 2001-03-07 | DEMIDOV GERMAN VIKTOROVICH; DAVLETSHIN RINAT FASIKHOVICH; ZARIPOV DAMIR VAZYKHOVICH; MURATOV RAVIL FATYKHOVICH; OSIPOV EDUARD SERAFIMOVICH; KUSHNAREV NIKOLAI DMITRIEVICH |
| A vehicle is proposed with an aerodynamic module (6) in the form of at least one toroidal rotating body. The cross section of the body in question in the plane passing through the axis (OO) of rotation has an aerodynamic profile aligned along the vehicle's direction of movement. | ||||||
| 31 | FLUGKÖRPER | EP96934787.0 | 1996-10-23 | EP0857139A1 | 1998-08-12 | Schier, Johannes |
| The invention concerns an aircraft (1) which has balanced torque and comprises a useful load container (6) and a propeller (5) which is disposed in a central axis (3) and is driven by a drive motor (4). The object of the invention is to provide an aircraft which, in a stable flying attitude and with simple control means, can convey useful loads. This object is achieved in that the central propeller (5) and, relative thereto, the motor (4) itself and/or a torque-balancing means disposed thereon are mounted so as to be rotatable in opposite senses and so as to be together rotatable relative to the useful load container. | ||||||
| 32 | A high-passenger capacity airplane | EP93108787.8 | 1993-06-01 | EP0578954A1 | 1994-01-19 | Abdurachmanovich, Muchamedov Fatidin |
The invention belongs to aeronautical engineering sphere and can be used in the design of the high-passenger capacity airplanes, and the airbuses of a blended layout, which can operate in passenger as well as in mixed cargo-passenger versions. The technical results provided by the realization of a given invention, are the following: the decrease of an airplane dimentions on retention of the required passenger capacity, the increase in fuel efficiency, an airplane mass reduction, the production costs cutting, the simplification of it's production, and also use of it in passenger and mixed versions. An airplane has the fuselage 1, the lifting center-section wing 2 in a disk form in plan and the outer wing panels 3. The V-tail 4 is designed separated. The passenger seats are housed in the fuselage 1, and an additional passenger or cargo compartment is designed within the lifting center-section wing 2, where passenger seats can be installed or cargo can be located. |
||||||
| 33 | TURBOCRAFT | EP91908875 | 1991-04-03 | EP0505509A4 | 1993-06-16 | VALVERDE, RENE, L. |
| An aircraft having a substantially circular body having a profile in the direction of flight as a profile of an airplane wing, at least two concentric counter-rotating turbo-blade assemblies (15) within said body for effecting a vertical lifting air stream through said assemblies (15). Power generating devices (6, 13, 21, 23) and devices (122, 123, 124, 126) for coupling the power generating devices to the turbo-blade assemblies (15) for maintaining them in rotary motion. It also includes thrusting devices (6, 18, 157) coupled to the power generating devices for applying horizontal thrust to the aircraft, retro-boosting devices (21, 169) including a plurality of combustion chambers (104) located below the turbo-blade assemblies for boosting said vertical lifting airstream. Also included is a compressed air plenum (106) disposed below said turbo-blade assemblies (15) in fluid communication with the combustion chambers (104) and to the intake portion of the power generating means for supplying oxygen for sustaining combustion in said combustion chambers (104) and for sustaining power in said power generating means (6, 13, 21, 23), including upper vanes (7, 101) disposed above said turbo-blade assemblies (15) for ingesting air, and lower vanes (24) disposed below said compressed air plenum (106) for exhausting air, and respective upper and lower vane control means (110). | ||||||
| 34 | GYRO STABILIZED FLYING SAUCER MODEL | EP81900122.0 | 1980-11-24 | EP0040636A1 | 1981-12-02 | MESSINA, Gene |
| Un modele ayant un corps en forme de soucoupe volante (111) pourvue de sustentation au moyen d'un dispositif de production de poussee tel qu'un moteur a turbine ou Wankel a mouvement alternatif (102) et une helice (101). On empeche le corps (111) de tourner a l'aide d'ailettes de contre-rotation (105A, B) et la stabilite dans le plan horizontal est assuree a l'aide d'un gyro rotor interne (104) actionne par l'ecoulement d'air provenant de l'helice (101). | ||||||
| 35 | "AIR WHEEL" ROTOR. GYRO-STABILIZED AIRCRAFT AND WIND-ENERGY INSTALLATION UTILIZING "AIR WHEEL" ROTOR, AND GROUND-BASED OR SHIP-BASED DEVICE FOR LAUNCHING SAME | EP14900825.2 | 2014-08-26 | EP3192738A1 | 2017-07-19 | KUZIKOV, Sergej Yurevich |
The group of inventions relates to aviation and wind energy, and specifically to designs of aircraft rotors and cruise propellers. An "Air Wheel" rotor, having blades with variable pitch and variable torsion, contains a closed wing which is connected to one or a plurality of coaxial bushings by means of torsionally-flexible blades, wherein the connection between the blades and the closed wing may be rigid, elastic or viscoelastic. A movable mounting of blades to the one or plurality of bushings is carried out by means of a torsion element, or by means of an axial hinge or by means of an offset axial hinge. The rotor contains a device for controlling the overall/cyclical pitch of the blades, which are set partially or fully by the relative positions (pan, tilt, shift) of the bushings. The blades may have a complex three-dimensional shape. The profile of the torsionally flexible blades may have a variable concavity. A variable torsional rigidity along a blade and/or a transverse bend allow for a hyperbolic blade rotation which maximally approximates the ideal blade rotation. The "air wheel" rotor has a wide range of applications. Design constraints for increasing flight speed are reduced. The efficiency, strength and durability of variable-pitch propellers are increased, losses and noise are decreased, and vibration is eliminated. |
||||||
| 36 | Aircraft, particularly small aircraft, having a propulsion system including a plurality of pulse detonation engines (PDEs) | EP04425043.9 | 2004-01-26 | EP1557356B1 | 2005-12-14 | Perlo, Piero; Golub, Victor; Kotelnikov, Andrei |
| 37 | Aircraft, particularly small aircraft, having a propulsion system including a plurality of pulse detonation engines (PDEs) | EP04425043.9 | 2004-01-26 | EP1557356A1 | 2005-07-27 | Perlo, Piero; Golub, Victor; Kotelnikov, Andrei |
A small aircraft is disclosed having a propulsion system including a plurality of Pulse Detonation Engines (PDEs). The engines are arranged within the wings (2a) of the aircraft. The discharge nozzles (8) of the detonation tubes (7) of the detonation engines are provided at different areas of the aircraft and are differently oriented, so as to provide extra manoeuvrability along the three directions. The arrangement of the detonation tubes (7) within the wings (2a) reduces drag and hence the fuel consumption. |
||||||
| 38 | FLUGKÖRPER | EP96934787.1 | 1996-10-23 | EP0857139B1 | 1999-04-07 | Schier, Johannes |
| The invention concerns an aircraft (1) which has balanced torque and comprises a useful load container (6) and a propeller (5) which is disposed in a central axis (3) and is driven by a drive motor (4). The object of the invention is to provide an aircraft which, in a stable flying attitude and with simple control means, can convey useful loads. This object is achieved in that the central propeller (5) and, relative thereto, the motor (4) itself and/or a torque-balancing means disposed thereon are mounted so as to be rotatable in opposite senses and so as to be together rotatable relative to the useful load container. | ||||||
| 39 | VEHICLE WITH AERODYNAMIC MODULE | EP96902019.7 | 1996-01-25 | EP0760338A1 | 1997-03-05 | DEMIDOV, German Viktorovich; DAVLETSHIN, Rinat Fasikhovich; ZARIPOV, Damir Vazykhovich; MURATOV, Ravil Fatykhovich; OSIPOV, Eduard Serafimovich; KUSHNAREV, Nikolai Dmitrievich |
A vehicle is proposed with an aerodynamic module (6) in the form of at least one toroidal rotating body. The cross section of the body in question in the plane passing through the axis (OO) of rotation has an aerodynamic profile aligned along the vehicle's direction of movement. |
||||||
| 40 | Fluggerät | EP92122020.8 | 1992-12-25 | EP0553490A1 | 1993-08-04 | Bucher, Franz |
Das Fluggerät besitzt einen angetriebenen, in einem Gehäuse (2) liegend angeordneten Rotor, mittels welchem eine Auftriebskraft erzeugbar ist, die das Gewicht des Fluggerätes übersteigt. Das Gehäuse ist im wesentlichen als Rundflügel ausgebildet. Im Bereich des Rotors sind Luftführungsmittel vorgesehen zur Beeinflussung des Rotorstrahls, womit die Lage und die Bewegungen im Schwebeflug steuerbar sind. Das Fluggerät kann vom Schwebeflug in einen angetriebenen Gleitflug übergehen. Für diesen Uebergang sowie den Gleitflug sind Leitwerkmittel (8, 8'; 11, 11') vorgesehen für die dynamische Erzeugung einer Steuerkraft. Diese können auch im (vergrösserten) Rundflügel integriert sein. Die Leitwerkmittel sind ausserhalb des Wirkbereiches des Rotorstrahls seitlich am oder im Gehäuse (2) angeordnet. Im angetriebenen Gleitflug wird der Vortrieb von einem Propeller (5) und der Auftrieb durch das Rundflügelprofil übernommen. |
||||||
