| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 101 | EJECTOR AND AIRFOIL CONFIGURATIONS | PCT/US2016044326 | 2016-07-27 | WO2017065858A3 | 2017-07-13 | EVULET ANDREI |
| A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface. | ||||||
| 102 | EJECTOR AND AIRFOIL CONFIGURATIONS | EP18165126.6 | 2016-07-27 | EP3363732A1 | 2018-08-22 | EVULET, Andrei |
A vehicle having a main body (504), a primary airfoil (503) coupled to the main body, a gas generator (501) coupled to the main body and producing a gas stream, a conduit (505) fluidly coupled to the generator, an ejector (502) fluidly coupled to the conduit and embedded in the primary airfoil, the ejector comprising an outlet structure out of which the gas stream flows at a predetermined adjustable velocity and a secondary airfoil (506) having a leading edge (507) and located directly downstream of the outlet structure such that the gas stream from the ejector flows over the leading edge of the secondary airfoil.
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| 103 | PROPULSION SYSTEM ASSEMBLY | EP15829823 | 2015-07-29 | EP3178154A4 | 2018-05-02 | 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. | ||||||
| 104 | AIRCRAFT ATTITUDE CONTROL METHODS | EP14893562 | 2014-05-30 | EP3111286A4 | 2017-04-12 | 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. | ||||||
| 105 | 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. | ||||||
| 106 | 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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| 107 | FLUGKÖRPER | EP12714935.9 | 2012-02-08 | EP2673192B1 | 2016-06-01 | Voss, Andreas |
| 108 | AN AEROSPACE PLANE SYSTEM | EP13883346 | 2013-04-04 | EP2834152A4 | 2015-12-23 | ALEXANDER NIC |
| 109 | PROPULSION DEVICE | EP06716806.2 | 2006-02-24 | EP1855941B1 | 2015-04-08 | MARTIN, Glenn, Neil |
| 110 | FLUGKÖRPER | EP12714935.9 | 2012-02-08 | EP2673192A1 | 2013-12-18 | Voss, Andreas |
| The invention relates to a remote-controlled small flying object comprising at least one lift area (17), comprising at least one pair of propeller drives (12, 13), and comprising a weight element (20), the position of which can be varied to vary the centre of gravity of this small flying object (10) in the longitudinal direction of the small flying object (10). In order to accomplish a more compact and robust design with improved flying characteristics, the lift area (17) of the small flying object (10) is arranged above a plane formed by the axes of rotation of the propeller drives (12, 13) to generate a lifting force for vertical takeoff and/or landing. | ||||||
| 111 | PROPULSION DEVICE | EP06716806.2 | 2006-02-24 | EP1855941A1 | 2007-11-21 | MARTIN, Glenn, Neil |
| A personal flight device (1) which consists of a housing (4) securable to a pilot, at least one pair of fans (2,3) and at least one engine (6) mounted on the housing for driving the fans; one fan of the pair is mounted to one side of the housing and the other fan of the pair is mounted to the other side of the housing; in use both fans rotate in the same direction for producing thrust. | ||||||
| 112 | SYSTEM AND METHOD FOR UTILIZING STORED ELECTRICAL ENERGY FOR VTOL AIRCRAFT THRUST ENHANCEMENT AND ATTITUDE CONTROL | EP05855311.6 | 2005-12-22 | EP1831073A2 | 2007-09-12 | PARKS, Robert |
| A system and method are provided for a short take-off and landing/vertical take-off and landing aircraft that stores required take-off power in the form of primarily an electric fan engine, and secondarily in the form of an internal combustion engine, wherein the combined power of the electric fan and internal combustion engines can cause the STOL/VTOL A/C to take-off in substantially less amount of time and space than other STOL/VTOL A/C, and further wherein the transition from vertical to horizontal thrust is carefully executed to rapidly rise from the take-off position to a forward flight position, thereby minimizing the necessity for a larger electric fan engine. | ||||||
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