公开(公告)号：EP3407703A1

公开(公告)日：2018-12-05

申请号：EP17744861.0

申请日：2017-01-26

申请人： JG Entrepreneurial Enterprises LLC

发明人： GOELET, John

IPC分类号： A01G15/00 ,  B64C39/02 ,  B64D1/16 ,  B64D1/18 ,  G05D1/10

CPC分类号： B64C39/02 ,  A01G15/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/12 ,  B64C2201/125 ,  B64C2201/146 ,  B64C2201/206 ,  B64D1/02 ,  B64D1/18 ,  B64D39/06 ,  B64D2211/00 ,  G05D1/0022

摘要： A weather modification system that includes both systems and vehicles capable of modifying the weather. The systems may include devices capable of utilizing compositions to create dispersants that can modify weather. The system is capable of autonomous weather modification where the vehicles may operate for long periods of time in the air and may be directed by a control station. The vehicles may include an airplane, a UAV, a balloon, a satellite, an airship, such as a lenticular airship, a helicopter or a lighter than air vehicle. The vehicles are capable of multiple functions including weather modification, weather monitoring, and coordination between different vehicles.

公开(公告)号：EP3401215A1

公开(公告)日：2018-11-14

申请号：EP18171228.2

申请日：2018-05-08

申请人： Pinnacle Vista, LLC

发明人： TU, Haofeng

IPC分类号： B64C29/00 ,  B64C39/12 ,  B64C27/26 ,  B64C27/82 ,  B64C39/02 ,  G05D1/02 ,  G05D1/04 ,  G05D1/08

CPC分类号： B64C27/26 ,  B64C27/82 ,  B64C29/0025 ,  B64C39/024 ,  B64C39/12 ,  B64C2027/8236 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165 ,  G05D1/0202 ,  G05D1/042 ,  G05D1/0858

摘要： A multi-copter lift body aircraft has a push or pull propeller (26) and a lift body (70) that has a first airfoil shape (71) on a front to rear cross-section and a second airfoil shape (72) on a left to right cross-section. The lift body (70) is made from a top shell and a bottom shell. The lift body (70) has a nose (22) and a tail (25). Multi-copter propellers (60) are attached to the lift body. The multi-copter propellers (60) provide a lift at low speeds and the lift body (70) provides a lift at high speeds. Avionics (68) can be stored in a hollow cavity of the lift body. The avionics (68) may include a control circuit (65), batteries (66), and a radio receiver. The multi-copter has a lift body (70) made from an upper shell (36, 38) and a lower shell (37, 39). The lift body (70) has an optimum attack angle (91) at a cruising speed, and the lift body provides a combined lift mode.

公开(公告)号：EP3124381B1

公开(公告)日：2018-10-24

申请号：EP16190021.2

申请日：2014-12-11

申请人： Korea Aerospace Research Institute

发明人： LEE, Sang-Cherl ,  KIM, Hae-Dong ,  GONG, Hyeon-Cheol ,  CHOI, Gi-Hyuk ,  HWANG, In-Hee ,  SUK, Byong-Suk

IPC分类号： B64C39/02 ,  B64F1/12 ,  B64F1/22

CPC分类号： B60L11/1824 ,  B60L2200/10 ,  B60L2230/10 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/108 ,  B64C2201/182 ,  B64C2201/201 ,  B64D45/08 ,  B64F1/00 ,  B64F1/005 ,  B64F1/12 ,  B64F1/222 ,  F21S8/086 ,  F21V33/00 ,  F21W2131/103 ,  F21Y2115/10

摘要： An apparatus and method for containing and charging an unmanned VTOL aircraft are disclosed. The apparatus for containing and charging an unmanned VTOL aircraft includes a post 110, an extended member 120, a cover 130, a fastening unit 140, and a charging unit 150. The post is placed on a ground. The extended member is connected to the post. The cover is provided on the extended member, and is configured to be opened or closed in order to contain and protect the unmanned VTOL aircraft. The fastening unit is provided in the cover, and is configured to fasten the unmanned VTOL aircraft. The charging unit is provided in the fastening unit, and is configured to charge the unmanned VTOL aircraft.

公开(公告)号：EP3378768A1

公开(公告)日：2018-09-26

申请号：EP18161486.8

申请日：2018-03-13

申请人： RIEDEL Communications International GmbH

发明人： Riedel, Thomas

IPC分类号： B64C39/02

CPC分类号： B64C39/022 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/06 ,  B64C2201/122 ,  B64C2201/148

摘要： Die Erfindung betriff unter anderem ein Fluggerät (10), umfassend wenigstens einen elektromotorischen Antrieb (11a, 11b) und eine Steuerung (12), mit der das Fluggerät eine eingestellte Flugposition dauerhaft bewahren kann, wobei das Fluggerät über eine Kabelanordnung (16) mit einer Bodenstation (19) verbindbar ist, und wobei die Kabelanordnung wenigstens zwei elektrische Leiter (17a, 17b) zur Bereitstellung einer Spannungsversorgung für den Antrieb umfasst, sowie ein Glasfaserkabel (18) zur Übermittlung von Daten und/oder Signalen.

公开(公告)号：EP3374263A1

公开(公告)日：2018-09-19

申请号：EP16864925.9

申请日：2016-11-09

申请人： Matternet, Inc.

发明人： RAPTOPOULOS, Andreas ,  BARUCHIN, Ido ,  HINKLE, Christopher, Winson ,  MA, Derek, X. ,  O'SULLIVAN, James, Standish

IPC分类号： B64D1/12 ,  B64C39/02 ,  B64D1/08 ,  B64D9/00 ,  B64F1/32 ,  G05D1/00

CPC分类号： B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/128 ,  B64C2201/208 ,  G08G5/0069 ,  G08G5/025

摘要： An unmanned aerial vehicle (UAV) for transporting a payload is provided. The UAV comprises a body and one or more propellers rotatably connected to the body. The UAV further comprises a battery mounted to the body. The battery is releasable from the bottom of the UAV. The UAV further comprises a payload container mounted to the body. The payload container is releasable from the bottom of the UAV to a landing platform associated with a UAV station.

公开(公告)号：EP3365227A1

公开(公告)日：2018-08-29

申请号：EP16788576.3

申请日：2016-09-21

申请人： Marganski, Edward ,  Izdebski, Andrzej

发明人： MARGA SKI, Edward

IPC分类号： B64C29/02 ,  B64C39/02 ,  B64C39/12

CPC分类号： B64C29/02 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108

摘要： The object of the invention is a vertical take-off and landing aircraft in the manned or unmanned version powered by one or more electric motors which rotate two contra-rotating, fixed-pitch or variable-pitch propellers located at the front. To control the aircraft during vertical and horizontal flights auxiliary horizontal and vertical control and trim surfaces (5) and (7), located in the slipstream of contra-rotating propellers (1) in front of the aircraft's centre of gravity are used, whereas the control and trim surfaces (5) and (7) are suspended in relation to the aircraft on axles (6) and (8) that are located in front of the centre of aerodynamic forces created by them, owing to which the aerodynamic surfaces place themselves in the direction of the flowing control air of the aircraft, while the lift force created by them depends directly on the moments exerted on their axes of rotation (6) and (8), created with the use of linear or angular magneto-dynamic hoists (10) or with the aerodynamic method through auxiliary control tabs (12) installed on the control and trim surfaces (5) and (7).

公开(公告)号：EP3213995A4

公开(公告)日：2018-07-25

申请号：EP15855700

申请日：2015-10-12

申请人： GUANGZHOU XAIRCRAFT TECH CO LTD

发明人： PENG BIN ,  XIAO DINGFENG

IPC分类号： H02K9/06 ,  B64C39/02 ,  B64D33/08

CPC分类号： B64C25/08 ,  B64C1/069 ,  B64C25/52 ,  B64C25/58 ,  B64C27/08 ,  B64C39/024 ,  B64C2025/325 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64D27/26 ,  B64D33/08 ,  H02K9/06

摘要： A rotorcraft together with a heat dissipation structure for a motor, a connecting structure for an arm and an airframe and an assembly and disassembly structure for a foot stand are provided. The rotorcraft includes: the airframe, the arm having a first end connected to the airframe, a propeller connected to the second end of the arm and driven by a motor, and the heat dissipation structure for the motor. The heat dissipation structure for the motor includes: a casing being a hollow structure having a top opening and an air inlet in a bottom portion, in which a motor body is disposed inside of the casing, and an air channel is formed between a circumferential edge of the motor body and an inner wall of the casing; a head cover connected to a revolving shaft of the motor synchronously and provided with a plurality of air flow picks on the lower surface thereof; and a mounting stand fixed to an upper surface of the head cover and configured to be connected with the propeller.

公开(公告)号：EP2773556B1

公开(公告)日：2018-07-18

申请号：EP12805568.8

申请日：2012-10-20

申请人： Airbus Defence and Space GmbH

发明人： HIEBL, Manfred ,  PONGRATZ, Hans Wolfgang

IPC分类号： B64C3/30 ,  B64C39/02

CPC分类号： B64C39/02 ,  B64C3/30 ,  B64C9/00 ,  B64C27/41 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/105 ,  B64C2201/122 ,  B64C2201/165 ,  B64D39/00 ,  B64D2041/005 ,  B64D2211/00 ,  Y02T50/55 ,  Y02T90/36

公开(公告)号：EP3339185A1

公开(公告)日：2018-06-27

申请号：EP16205978.6

申请日：2016-12-21

申请人： Airbus Defence and Space GmbH

发明人： Steinwandel, Jürgen ,  HOFMANN, Michael ,  JUDAS, Michael

IPC分类号： B64D45/02 ,  B64D35/00 ,  H01T7/00 ,  B64C39/02 ,  B64D27/24

CPC分类号： B64D27/24 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/165 ,  B64D29/00 ,  B64D35/00 ,  B64D45/02 ,  H01T4/08 ,  H01T4/10 ,  H01T7/00 ,  H02K7/083 ,  H02K11/26 ,  H05K9/0047 ,  Y02T50/62

摘要： Zur Verbesserung der Betriebssicherheit bei vereinfachter Konstruktion unter widrigen Witterungsbedingungen schafft die Erfindung eine Luftfahrzeugantriebsvorrichtung (10) zum Erzeugen eines Vortriebs und/oder Auftriebs eines Luftfahrzeuges, umfassend eine Drehwelle (12), ein Drehwellenlager (14, 16), eine Drehwellenantriebsmaschine (18) zum drehenden Antreiben der Drehwelle (12) und ein Gehäuse (20), wobei das Drehwellenlager (14, 16) und die Drehwellenantriebsmaschine (18) in einen Innenraum des Gehäuses (44) angeordnet sind und die Drehwelle (12) durch eine Gehäuseöffnung (42) des Gehäuses (20) nach außerhalb des Gehäuses (20) ragt, wobei im Bereich der Gehäuseöffnung (42) eine Überspannungsableitungseinrichtung (52) angeordnet ist, die zum Ableiten einer auf der Drehwelle (12) anliegenden Überspannung ausgebildet ist.

公开(公告)号：EP3272652A4

公开(公告)日：2018-05-23

申请号：EP17749346

申请日：2017-05-26

申请人： UVIFY CO LTD

发明人： LIM HYON

IPC分类号： B64C39/02 ,  B64C27/08 ,  B64C27/12 ,  B64D35/02 ,  B64D47/08

CPC分类号： B64C27/08 ,  B64C27/12 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/127 ,  B64D35/02 ,  B64D47/08

摘要： An unmanned aerial vehicle includes a plurality of arm units, each having a rotary wing, a motor, and an arm main body and detachably coupled to a main body; the main body having a plurality of receptacles for coupling to the arm units; and a battery unit detachably coupled to the main body to be exposed to outside, in which at least a part of the battery unit is exposed to outside when the battery unit is coupled to the main body.