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1. 发明授权

EP3922549B1 AIRCRAFT 审中-实审
公开(公告)号：EP3922549B1
公开(公告)日：2024-10-30
申请号：EP21173725.9
申请日：2021-05-13
IPC分类号： B64C3/00 , B64C11/46 , B64C3/32 , B64D27/02 , B64C3/56
CPC分类号： B64C3/00 , B64C11/46 , B64C3/56 , B64C3/32 , B64D27/02 , Y02T10/70 , Y02T50/40 , Y02T50/60 , B64D27/026

2. 发明公开

EP4375496A3 VANE ASSEMBLY FOR AN UNDUCTED THRUST PRODUCING SYSTEM 审中-实审
公开(公告)号：EP4375496A3
公开(公告)日：2024-10-09
申请号：EP24169542.8
申请日：2013-10-23
申请人： General Electric Company
发明人： BREEZE-STRINGFELLOW, Andrew , ZATORSKI, Darek Tomasz , CEDAR, Richard David
IPC分类号： F01D5/14 , B64C11/18 , B64C11/46 , F02K3/02 , F02C6/20 , F03D1/06 , B64D33/02 , B64D33/04 , F02K1/46 , F02C7/36
CPC分类号： B64C11/46 , F02K3/025 , F02C6/206 , F05B2240/1220130101 , F05B2260/9620130101 , F05D2220/32520130101 , F05D2250/3020130101 , F05D2260/1420130101 , F05D2220/32420130101 , F05D2250/5220130101 , F02K1/46 , F05D2250/5120130101 , B64C11/18 , Y02E10/72 , B64C11/00 , F05D2260/4031120130101 , F02C7/36 , F05D2250/7020130101 , F05D2220/9020130101 , F05D2240/30120130101 , Y02T50/60
摘要： A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.

3. 发明公开

EP2903895A4 ELECTRICALLY POWERED AERIAL VEHICLES AND FLIGHT CONTROL METHODS 有权
标题翻译：电动飞机的飞行控制程序
公开(公告)号：EP2903895A4
公开(公告)日：2016-06-01
申请号：EP13843351
申请日：2013-10-04
申请人： SKYKAR INC , LENG MARCUS
发明人： LENG MARCUS
IPC分类号： B64C29/00 , B64C29/02 , B64C39/02
CPC分类号： B64C27/26 , B60L11/1805 , B60L11/1859 , B60L11/1861 , B64C1/26 , B64C11/46 , B64C15/02 , B64C29/00 , B64C29/0025 , B64C29/02 , B64C39/026 , B64D17/00 , B64D27/24 , B64D31/12 , B64D33/08
摘要： An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control.

4. 发明公开

EP3000722A1 AIRCRAFT 有权
标题翻译： LUFTFAHRZEUG
公开(公告)号：EP3000722A1
公开(公告)日：2016-03-30
申请号：EP15185159.9
申请日：2015-09-15
申请人： Rolls-Royce plc
发明人： Moxon, Matthew
IPC分类号： B64C3/38 , B64C3/52 , B64C29/00
CPC分类号： B64C11/008 , B64C3/385 , B64C3/52 , B64C11/46 , B64C29/0033 , B64D45/00 , B64D2045/0085 , Y02T50/14
摘要： An aircraft (40). The aircraft comprises a plurality of propellers (46) mounted to wings (44). Each propeller comprises at least one blade (72, 74) coupled to a respective propeller cyclic actuator (78) configured to cyclically alter the pitch of the respective blade (72, 74) as the propeller rotates. The aircraft (40) is configured such that provision of cyclic pitch to the propeller (46) twists at least a portion of the wing (44) about a span of the wing (46) relative to the fuselage (42), to thereby adjust the local angle of incidence of the wing (46).
摘要翻译：飞机（40）。飞行器包括安装到机翼（44）上的多个螺旋桨（46）。每个螺旋桨包括联接到相应的螺旋桨循环致动器（78）的至少一个叶片（72,74），所述叶片构造成在推进器旋转时周期性地改变相应叶片（72,74）的桨距。飞行器（40）构造成使得向螺旋桨（46）提供循环桨距绕机翼（46）相对于机身（42）的跨度扭转翼（44）的至少一部分，从而调整机翼的局部入射角（46）。

5. 发明公开

EP2903895A1 ELECTRICALLY POWERED AERIAL VEHICLES AND FLIGHT CONTROL METHODS 有权
标题翻译：电动飞机的飞行控制程序
公开(公告)号：EP2903895A1
公开(公告)日：2015-08-12
申请号：EP13843351.1
申请日：2013-10-04
申请人： Skykar Inc. , Leng, Marcus
发明人： LENG, Marcus
IPC分类号： B64D27/24 , B64C27/22 , B64C27/28 , B64C29/00 , B64C39/08
CPC分类号： B64C27/26 , B60L50/52 , B60L58/12 , B60L58/14 , B64C1/26 , B64C11/46 , B64C15/02 , B64C29/00 , B64C29/0025 , B64C29/02 , B64C39/026 , B64D17/00 , B64D27/24 , B64D31/12 , B64D33/08
摘要： An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control.

6. 发明公开

EP3401216A1 SYSTEMS AND METHODS FOR ACOUSTIC RADIATION CONTROL 有权
公开(公告)号：EP3401216A1
公开(公告)日：2018-11-14
申请号：EP18169650.1
申请日：2018-04-26
申请人： Aurora Flight Sciences Corporation
发明人： KEARNEY-FISCHER, Martin
IPC分类号： B64C39/02
CPC分类号： B64C27/57 , B64C11/305 , B64C11/46 , B64C39/024 , B64C2201/024 , B64C2220/00 , G10K11/175 , G10K2200/10 , G10K2210/1281
摘要： Disclosed is a system for controlling acoustic radiation from an aircraft. The system comprising a plurality of rotor systems (one or more) and a noise controller configured to regulate acoustic radiation from the plurality of rotor systems. The noise controller can be configured to regulate a commanded flight setting from the flight control system and to output a regulated flight setting to the plurality of rotor systems. Based on the regulated flight setting, the plurality of rotor systems are configured to generate, individually and in aggregate, acoustic radiation having a target acoustic behavior. The target acoustic behavior may be achieved using beamforming techniques to, for example, change the directionality of acoustic radiation from the plurality of rotor systems, or otherwise tune the acoustic radiation to reduce detectability and/or annoyance.

7. 发明公开

EP3259184A1 VEHICLE CONFIGURATION WITH MOTORS THAT ROTATE BETWEEN A LIFTING POSITION AND A THRUSTING POSITION 有权
标题翻译：使用电动机在提升位置和推力位置之间旋转的车辆配置
公开(公告)号：EP3259184A1
公开(公告)日：2017-12-27
申请号：EP16708045.6
申请日：2016-02-18
申请人： Amazon Technologies, Inc.
发明人： WELSH, Ricky Dean
IPC分类号： B64C39/02
CPC分类号： B64C27/52 , B62D63/04 , B63B1/32 , B63B2035/006 , B63H25/00 , B64C11/46 , B64C27/28 , B64C39/024 , B64C2201/021 , B64C2201/024 , B64C2201/027 , B64C2201/108 , B64C2201/128 , B64C2201/165 , B64G1/10 , B64G1/22
摘要： This disclosure describes a configuration of an unmanned aerial vehicle ("UAV") (100) that will facilitate extended flight duration. The UAV may have any number of lifting motors (102). For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (also known as an octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a pivot assembly (109) that may rotate about an axis (624) from a lifting position to a thrusting position. The pivot assembly may include two or more offset motors (610) that generate a differential force that will cause the pivot assembly to rotate between the lifting position and the thrusting position without the need for any additional motors or gears.

8. 发明公开

EP3176079A1 ANTRIEBSVORRICHTUNG FÜR EINEN GLEITSCHIRM 有权转让
标题翻译：驱动装置的飞行伞
公开(公告)号：EP3176079A1
公开(公告)日：2017-06-07
申请号：EP16196123.0
申请日：2016-10-27
申请人： SKY SPORT INTERNATIONAL PVT LTD.
发明人： KURRLE, Ulrich
IPC分类号： B64C11/46 , B64C31/036 , B64D27/24 , B64D35/06
CPC分类号： B64C31/036 , B64C11/46 , B64D27/24 , B64D35/06 , Y02T50/62
摘要： Die vorliegende Erfindung betrifft eine Antriebsvorrichtung (1) für einen Gleitschirm (2), einen Gleitschirm (2) mit Antriebsvorrichtung (1) und ein Verfahren zum Starten eines Gleitschirmes (2). Um ein Starten und Fliegen des Gleitschirmes (2) besonders effizient und sicher zu gestalten, schlägt die vorliegende Erfindung vor, dass in einem Flugbetrieb des Gleitschirmes (2) ein erster Propeller (6) der Antriebsvorrichtung (1) links von dem Piloten und ein zweiter Propeller (7) der Antriebsvorrichtung (1) rechts von dem Piloten angeordnet sind und während des Startens ein Umorientieren der Propeller stattfindet.

9. 发明公开

EP2912271A2 UNDUCTED THRUST PRODUCING SYSTEM ARCHITECTURE 有权
标题翻译： ROHRLOSE SCHUBERZEUGUNGSSYSTEMARCHITEKTUR
公开(公告)号：EP2912271A2
公开(公告)日：2015-09-02
申请号：EP13844584.6
申请日：2013-10-23
申请人： General Electric Company
发明人： ZATORSKI, Darek, Tomasz , HAMEL, Jeffrey, Anthony
IPC分类号： F01D5/14 , B64C11/18 , B64C11/46 , F02K3/02 , F02C6/20 , F03D1/06 , B64D33/02 , B64D33/04 , F02K1/46
CPC分类号： F01D17/16 , B64C11/001 , B64C11/18 , B64C11/46 , B64C11/48 , F01D9/02 , F02C6/206 , F02K1/46 , F02K3/025 , F05B2240/12 , F05B2260/96 , F05D2220/324 , F05D2220/325 , F05D2250/30 , F05D2250/51 , F05D2250/52 , F05D2260/14 , Y02E10/721 , Y02T50/66 , Y02T50/671
摘要： An unducted thrust producing system has a rotating element with an axis of rotation and a stationary element. The rotating element includes a plurality of blades each having a blade root proximal to the axis, a blade tip remote from the axis, and a blade span measured between the blade root and the blade tip. The rotating element has a load distribution such that at any location between the blade root and 30% span the value of &Dgr;RCu in the air stream is greater than or equal to 60% of the peak &Dgr;RCu in the air stream.

10. 发明公开

EP2776315A1 SENKRECHT STARTENDES FLUGZEUG 有权转让
标题翻译：垂直起降飞机
公开(公告)号：EP2776315A1
公开(公告)日：2014-09-17
申请号：EP13753588.6
申请日：2013-07-19
申请人： Hesselbarth, Jonathan
发明人： Hesselbarth, Jonathan
IPC分类号： B64C29/00
CPC分类号： B64C29/0033 , B64C11/46 , B64C29/0075 , B64D27/26
摘要： The invention relates to a vertical-takeoff aircraft (1) with a wing (3). A first drive unit (4) and a second drive unit (5) are swivellably mounted on the wing (3). The first drive unit (4) and the second drive unit (5) are arranged on the wing (3) at a distance from a wing-end (12) of the wing (3). A first distance between the first drive unit (4) and a longitudinal axis (10) of the aircraft (3) is approximately equal to a second distance between the second drive unit (5) and the longitudinal axis (10) of the aircraft (3). The first drive unit (4) and the second drive unit (5) are swivellable into a horizontal flying position and a vertical flying position. In the horizontal flying position the first drive unit (4) is arranged above a wing surface and the second drive unit (5) below the wing surface on the wing. In the vertical flying position the first drive unit (4) and the second drive unit (5) are arranged in an approximately horizontal plane. The first drive unit (4) and the second drive unit (5) each have a swivel arm (7), wherein the swivel arms (7) are swivellably mounted on the wing (3).

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