| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 201 | An Aircraft | EP12191750.4 | 2012-11-08 | EP2597038A3 | 2015-11-25 | Rolt, Andrew; Thompson, Christopher |
An aircraft (10) comprises a wing (12) having a trailing edge (34), a suction surface (14) and a pressure surface (16). The aircraft (10) further comprises a propulsor device (22) having a first inlet (24) and an outlet (30) defined by a passageway. The first inlet (24) is located so as to ingest boundary layer air (56) adjacent the suction surface (14), and the outlet (30). The outlet (30) is located downstream of the trailing edge (34) of the wing (12).
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| 202 | An Aircraft | EP12191748.8 | 2012-11-08 | EP2597037A3 | 2015-11-25 | Rolt, Andrew; Thompson, Christopher |
An aircraft comprises a propulsive fan arrangement (18) having an intake (50) and an exhaust (52). The fan arrangement (18) is mounted adjacent a gas washed surface of the aircraft in the form of a suction surface (14) of a wing (12). The intake (50) is separated from the suction surface (14) to define a channel (20) therebetween. The aircraft further comprises a Venturi device (22) positioned downstream of the fan exhaust (52) to draw boundary layer air (56) through the channel (20).
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| 203 | AIRCRAFT WITH FREEWHEELING ENGINE | EP13813670.0 | 2013-03-27 | EP2836428A1 | 2015-02-18 | Smith, Frick A. |
| An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft. | ||||||
| 204 | Aerospace vehicle yaw generating tail section | EP11172334.2 | 2011-07-01 | EP2412628A2 | 2012-02-01 | Edwards, Huw Llewelyn; Husband, Stephen Mark; Fletcher, Paul |
A tail section (251) for an aerospace vehicle is provided. The tail section (251) comprises a rudder (253) which is movable about an axis to generate a yawing moment on the aerospace vehicle. The tail section (251) further comprises a thruster (257) having, in flow series, an air intake, an electrically powered device for accelerating the air received through the intake, and an air outlet which directs the accelerated air to increase the yawing moment generated by the rudder (253).
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| 205 | Lift and propulsion system for aircraft with vertical take-off and landing | EP06380206.0 | 2006-07-19 | EP1759988A3 | 2007-11-14 | Garcia Perez, Francisco Angel; Munoz Saiz, Manuel |
Lifting and propulsion system for aircraft with vertical take-off and landing that consists of applying to the aircraft certain propeller engines and rotating lifting systems around the transversal shafts and near the centre of gravity, presenting pairs of stabilizing propellers, turbines or fans in counter-rotation activated by electrical motors on the tips of the wings, nose and stabilizers on the tail of the aircraft, the electrical motors are powered by batteries, supercondensators, high powered electrical generators activated by the engines and by special auxiliary power units.
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| 206 | Lift and propulsion system for aircraft with vertical take-off and landing | EP06380206.0 | 2006-07-19 | EP1759988A2 | 2007-03-07 | Garcia Perez, Francisco Angel; Munoz Saiz, Manuel |
Lifting and propulsion system for aircraft with vertical take-off and landing that consists of applying to the aircraft certain propeller engines and rotating lifting systems around the transversal shafts and near the centre of gravity, presenting pairs of stabilizing propellers, turbines or fans in counter-rotation activated by electrical motors on the tips of the wings, nose and stabilizers on the tail of the aircraft, the electrical motors are powered by batteries, supercondensators, high powered electrical generators activated by the engines and by special auxiliary power units.
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| 207 | DUCTED AIR POWER PLANT | EP03761692.7 | 2003-06-27 | EP1534590A1 | 2005-06-01 | BRYANT, Ashley Christopher |
| A ducted air power plant, comprising a motor driven fan (7) situated in a duct (4), the fan (7) having an air intake side and in operation providing a high pressure air stream in the duct, and the fan being located adjacent air splitter means (18), the air splitter means (18) being arranged to divert the air stream into two or more subsidiary streams for delivery to respective jet nozzles (9) of the plant. The plant may be used in a vehicle such as an aircraft in order to provide a vertical take-off and hover capability as well a level flight power source. | ||||||
| 208 | Strömungskanal kurzer Baulänge | EP84105407.5 | 1984-05-12 | EP0126399A1 | 1984-11-28 | Morschheuser, Wilhelm Fritz |
Die Erfindung bezieht sich auf einen Strömungkanal von kurzer Baulänge. Ein derartiger Strömungskanal soll eine Verzweigung des Gasstromes ermöglichen, so daß beispielsweise die Brennkammern von Turbinen versorgt oder eine vor Niederschlägen geschützte Dachentlüftung vorgenommen werden können. Der Gasstrom gelangt dabei über einen Eintrittskanal (7) nach Aufteilung mittels eines Trennkeils in zwei Verzweigungskanäle (12). Ein derartiger Strömungskanal wird strömungstechnisch umso verlustreicher, je kürzer er ausgeführt wird. In diesem Fall lassen sich die Verluste weitgehend vermeiden, wenn die Verzweigungskanäle (1, 2) erfindungsgemäss sich zunächst zunehmend bis zu ihrer Umlenkung (3, 4) einschnüren. Im Bereich ihrer Umlenkung (3, 4) sind Leitschaufeln (5, 6) vorgesehen, und im Anschluß an die Umlenkung (3, 4) erfahren die Verzweigungskanäle (1, 2) wiederum eine stetige Erweiterung. Die Leitschaufeln (5, 6) sind verschwenkbar gelagert, so daß sie auch zur Absperrung der Verzweigungskanäle (1,2) verwendet werden können. |
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| 209 | WING TILT ACTUATION SYSTEM FOR ELECTRIC VERTICAL TAKE-OFF AND LANDING (VTOL) AIRCRAFT | EP18859571.4 | 2018-09-06 | EP3684688B1 | 2024-06-26 | MOORE, Andrew Dudley |
| A vertical take-off and landing (VTOL) aircraft (10) comprises a fuselage (24) first and second forward wings (20, 22) and first and second rearward wings (30, 32), each wing having a fixed leading edge (25, 35) and a trailing control surface (50) which is pivotal about a generally horizontal axis. Electric rotors (60) are mounted to the wings (20, 22, 30, 32), the electric rotors (60) being pivotal with the trailing control surface (50) between a first position in which each rotor (60) has a generally vertical axis of rotation, and a second position in which each rotor (60) has a generally horizontal axis of rotation;wherein at least one of the wings (20, 22, 30, 32) has a first and a second electric rotor (60) which are each mounted having non-parallel axes of rotation so that the thrust lines of the first and second electric rotors are different. | ||||||
| 210 | UNITÉ MOBILE | EP22727765.4 | 2022-05-02 | EP4384443A1 | 2024-06-19 | Merrien, Jean Paul |
| 211 | VERTICAL-TAKE-OFF AERIAL VEHICLE WITH AEROFOIL-SHAPED INTEGRATED FUSELAGE AND WINGS | EP20955476.5 | 2020-09-29 | EP4223636A4 | 2024-05-15 | Filho, Alberto Carlos Pereira |
| VERTICAL TAKE-OFF AIR VEHICLE WITH BLENDED AIRFOIL FUSELAGE AND WINGS, object of this application, essentially consists of a fixed-wing aircraft comprised of an airfoil-shaped fuselage (02) with four wings (10) shaped by the same airfoil. Accordingly, the fuselage has an aerodynamic wing behavior contributing to lift and minimizing drag of the aircraft, which provides greater payload and greater flight autonomy, in addition to good flight safety due to gliding during the horizontal flight. On each wing tip there is installed a thruster (35) (electric, ducted fan, turbojet/fan, or even a propeller) capable of turning, tilting longitudinally relative to the shaft of the aircraft, independently, by means of a rotary control system of the thrusters (35). This system is comprised of a driveshaft (34) installed on each wing and its corresponding electric motor (30). The thrusters (35) are all identical in performance, weight, and size, as a form of minimizing manufacturing costs, but the thrusters of the wings to the left rotate in a counter direction to those of the wings to the right to stabilize (neutralize) the wing tip vortex effect and torque due to the rotary moments caused by the rotary set of each thruster. A single control center commands both the rotation of the thrusters and the traction thereof, providing total control of the aircraft by vectoring and rotation, without the need to use control surfaces. The present model is innovative in its design generated from an airfoil that blends the entire fuselage and wings, presenting a hybrid behavior, as it performs the tasks of a VTOL vehicle, of a helicopter, as well as a conventional fixed-wing aircraft, being versatile in its abilities of vertical landing/take-off, gliding, vertical flight forwards and backwards, and horizontal flight with maximum economy. | ||||||
| 212 | IMPROVED THRUST SYSTEMS | EP21201064.9 | 2017-12-07 | EP3957560B1 | 2023-11-15 | ZAPATA, Frankie; ZAPATA, Chrystelle |
| 213 | AERIAL FLUID SPRAYING SYSTEM | EP19754714.4 | 2019-02-13 | EP3737608B1 | 2023-07-05 | FIDELER, Brian L.; KUNDEM, Jeshwanth |
| 214 | FLUIDIC PROPULSIVE SYSTEM | EP20802173.3 | 2020-01-21 | EP3911569A2 | 2021-11-24 | EVULET, Andrei |
| An aircraft includes a fuselage and at least one primary wing having an upper surface, at least one recess in the upper surface and at least one conduit in fluid communication with the at least one recess. At least one ejector is disposed within the at least one recess and is configured to receive compressed air via the at least one conduit. | ||||||
| 215 | AERIAL FLUID SPRAYING SYSTEM | EP19754714.4 | 2019-02-13 | EP3737608A4 | 2021-09-29 | FIDELER, Brian L.; KUNDEM, Jeshwanth |
| 216 | PROPULSION SYSTEM ASSEMBLY | EP15829823.2 | 2015-07-29 | EP3178154B1 | 2021-04-14 | REGEV, Eyal |
| A propulsion system assembly is provided including a driveshaft and a plurality of electric motor modules. The driveshaft is rotatably mounted to a casing about a drive axis, the driveshaft including a first shaft end and an opposite facing second shaft end. The plurality of electric motor modules are in axially stacked relationship with one another with respect to the drive axis to define an electric motor module stack, each electric motor module being configured for transmitting a torque to the driveshaft when coupled thereto independently of at least one other electric motor module. Each electric motor module includes a controllable clutch arrangement for selectively coupling and decoupling the respective electric motor module with respect to the driveshaft to respectively enable and disable transmission of torque between the respective electric motor module and the driveshaft. | ||||||
| 217 | PERSONAL PROPULSION APPARATUS AND METHOD | EP12809317.6 | 2012-12-18 | EP2794037B1 | 2017-08-09 | CONTORET, Adam Edward Alexander |
| 218 | AIRCRAFT ATTITUDE CONTROL METHODS | EP14893562.0 | 2014-05-30 | EP3111286A1 | 2017-01-04 | YU, Yun |
| Systems and methods are provided for aircraft attitude control. The aircraft attitude control may take physical parameters of the aircraft into account. For example, one or more aircraft configuration parameters, such as moment of inertia, motor lift curve, and/or axial distance may be calculated and/or taken into account based on the aircraft physical parameters. The aircraft configuration parameters may include non-linear parameters. The control systems may include feedback control systems, and may optionally use a feedforward and feedback control for angular acceleration. | ||||||
| 219 | AIRCRAFT | EP16166183.0 | 2016-04-20 | EP3093235A1 | 2016-11-16 | Moxon, Matthew |
An aircraft (10) comprises trailing edge flaps (17), a wing mounted propulsor (26) positioned such that the flaps (17) are located in a slipstream of the first propulsor in use when deployed. The aircraft (10) further comprises a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane. The thrust vectorable propulsor comprises a ducted fan (30) configurable between a first mode, in which the fan (30) provides net forward thrust to the aircraft (10), and a second mode in which the fan (30) provides net drag to the aircraft. (10). The fan (30) is positioned to ingest a boundary layer airflow in use when operating in the first mode.
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| 220 | FLUGKÖRPER | EP12714935.9 | 2012-02-08 | EP2673192B1 | 2016-06-01 | Voss, Andreas |
