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11. 发明公开

EP4400932A1 METHOD OF OPERATING AN AERIAL VEHICLE AND CONTROLLER 审中-实审
公开(公告)号：EP4400932A1
公开(公告)日：2024-07-17
申请号：EP23151509.9
申请日：2023-01-13
申请人： Lilium eAircraft GmbH
发明人： Machanek, Valentin , Dodenhöft, Jens
IPC分类号： G05D1/08 , B64C11/46 , B64D31/06
CPC分类号： B64C29/0033 , B64C39/12 , B64C11/46 , B64C13/16 , B64D31/06 , G05D2109/2420240101 , G05D2105/2220240101 , G05D1/49
摘要： A method of operating an aerial vehicle (1), the aerial vehicle (1) comprising a plurality of propulsion units (4, 5) arranged to be pivotable about at least one axis along an angular position and configured to generate a thrust force and/or a lift force, wherein the angular position and/or the thrust force of the plurality of propulsion units (4, 5) are controlled based on a translational movement related command, in particular, a force command, of the aerial vehicle (1) regarding at least one degree of freedom and a rotational movement related command, in particular, a moment command of the aerial vehicle (1) regarding at least one degree of freedom. In order to ensure flight safety, if it is determined that a combination of the translational movement related command and the rotational movement related command causes a saturation in the angular position and/or the thrust force of at least one of the plurality of propulsion units (4, 5), the translational movement related command is adjusted in at least one degree of freedom such that the rotational movement related command is met.

12. 发明公开

EP4375496A2 VANE ASSEMBLY FOR AN UNDUCTED THRUST PRODUCING SYSTEM 审中-实审
公开(公告)号：EP4375496A2
公开(公告)日：2024-05-29
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： F02C6/20
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.

13. 发明公开

EP4324745A3 SYSTEMS AND METHODS FOR CONTROLLING AN ELECTRIC VERTICAL TAKE-OFF AND LANDING AIRCRAFT 审中-实审
公开(公告)号：EP4324745A3
公开(公告)日：2024-05-15
申请号：EP23220866.0
申请日：2022-01-24
申请人： Archer Aviation, Inc.
发明人： BOWER, Geoffrey, C. , XUE, Nansi , CHEN, Alan , GOLDMAN, Benjamin , DEPENBUSCH, Nathan
IPC分类号： B64C29/00 , B64C11/50 , B64C11/46 , B64C11/30 , B64D27/24 , B64D27/357 , B64D31/16
CPC分类号： B64C29/0033 , B64C2220/0020130101 , B64C11/46 , B64C11/30 , Y02T50/60 , B64D27/357 , B64D31/16
摘要： A method of controlling an electric aircraft that has a plurality of actuators that includes a plurality of electric propulsion units includes: receiving force and moment commands for the electric aircraft; determining control commands for the plurality of actuators based on the desired force and moment commands by solving an optimization problem that comprises a noise minimization term for minimizing noise generated by the electric propulsion units; and controlling the plurality of actuators according to the determined control commands to meet the force and moment commands for the electric aircraft.

14. 发明授权

EP3000722B1 AIRCRAFT 有权
公开(公告)号：EP3000722B1
公开(公告)日：2018-12-26
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).

15. 发明公开

EP3354560A1 A THRUST PRODUCING UNIT WITH AT LEAST TWO ROTOR ASSEMBLIES AND A SHROUDING 有权
公开(公告)号：EP3354560A1
公开(公告)日：2018-08-01
申请号：EP18152689.8
申请日：2018-01-22
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： MORES, Sebastian , KIESEWETTER, Uwe , BEBESEL, Marius
IPC分类号： B64C11/00 , B64C29/00 , B64C27/20
CPC分类号： B64C11/46 , B64C11/001 , B64C27/08 , B64C27/20 , B64C29/0033
摘要： The invention is related to a thrust producing unit 3d for producing thrust in a predetermined direction 23, comprising a shrouding 6d and at least two rotor assemblies 7d, 8d, wherein the shrouding 6d defines an internal volume 20c, and wherein a first rotor assembly 7d of the at least two rotor assemblies 7d, 8d defines a first rotor axis and a second rotor assembly 8d of the at least two rotor assemblies 8d defines a second rotor axis, the first and second rotor axes 12d being one of: (i) coaxially arranged, and (ii) inclined by associated inclination angles 21a, 22a with respect to the predetermined direction 23, the associated inclination angles 21a, 22a being comprised in a range between -60° and +60°, and preferably amounting to 0°, and wherein the first rotor assembly 7d is arranged outside of the internal volume 20c of the shrouding 6d.

16. 发明公开

EP2912270A1 UNDUCTED THRUST PRODUCING SYSTEM 有权
标题翻译： ROHRLOSES SCHUBERZEUGUNGSSYSTEM
公开(公告)号：EP2912270A1
公开(公告)日：2015-09-02
申请号：EP13786120.9
申请日：2013-10-23
申请人： General Electric Company
发明人： BREEZE-STRINGFELLOW, Andrew , KHALID, Syed, Arif , SMITH, Leroy, Harrington, Jr.
IPC分类号： F01D5/14 , B64C11/18 , B64C11/46 , F02K3/02 , F02C6/20 , F03D1/06
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 ΔRCu in the air stream is greater than or equal to 60% of the peak ΔRCu in the air stream.

17. 发明授权

EP3790798B1 ELECTRIC TILTROTOR AIRCRAFT 有权转让
公开(公告)号：EP3790798B1
公开(公告)日：2024-09-18
申请号：EP19799480.9
申请日：2019-05-10
IPC分类号： B64C27/22 , B64C27/28 , B64C29/00 , B64D27/24 , B64C27/52 , B64C11/46 , B64C5/02
CPC分类号： B64C27/28 , B64C29/0033 , B64D27/24 , B64C11/46

18. 发明公开

EP4414261A1 AIRCRAFT 审中-实审
公开(公告)号：EP4414261A1
公开(公告)日：2024-08-14
申请号：EP23156103.6
申请日：2023-02-10
申请人： Lilium eAircraft GmbH
发明人： Onodi, Peter , Smith, Adam , Lim, Chia Hui , Ugarte, Inigo , Wilkosz, Benjamin Eduard
IPC分类号： B64C29/00 , B64D27/24 , B64D29/02 , B64D33/02 , B64C7/02 , B64C11/00 , B64C11/46
CPC分类号： B64C29/0033 , B64D29/02 , B64D33/02 , B64C11/001 , B64C7/02 , B64C11/46 , B64D27/31 , B64D27/34
摘要： An aircraft (1) comprises at least two propulsion units (4, 5) being pivotable provided on the aircraft (1), the propulsion units (4, 5) being arranged adjacent to each other along an arrangement direction and respectively comprising: a propulsion rotor (41) being rotatable about a rotation axis (42), configured to contribute in thrust generation, and configured to suck air along an airflow direction substantially perpendicular to the arrangement direction; a duct (43) configured to guide air to the propulsion rotor, the duct (43) comprises a non-circular inlet portion (44), a circular downstream portion (47) being substantially circular about the rotation axis (42) and being located downstream of the inlet portion (44) along the airflow direction, and an air guiding portion (46) guiding air from the non-circular inlet portion (44) to the circular downstream portion (47) and establishing the transition therebetween, the air guiding portion (46) having an upper (46a) and a lower air guiding portion (46b) which are spaced apart from each other and provided on respective upper and lower sides of the rotation axis (42). In order to enhance performance, the aircraft (1) further comprises at least one septum (7) which is interposed between two rotation axes (42) of two adjacent propulsion rotors (41), the at least one septum (7) extending on the upstream side along the airflow direction with respect to the circular downstream portion (47) and between the upper and lower air guiding portions (46a, 46b), the at least one septum having a guiding surface (71) having at least one tangential plane parallel to the rotation axis (42), and preferably perpendicular to the arrangement direction.

20. 发明公开

EP3375707A1 AIRCRAFT AND FLIGHT SYSTEM 有权转让
公开(公告)号：EP3375707A1
公开(公告)日：2018-09-19
申请号：EP18161784.6
申请日：2018-03-14
申请人： Ricoh Company Ltd.
发明人： SAKUMA, Hideomi
IPC分类号： B64C11/46 , B64C29/02
CPC分类号： B64C29/02 , B64C11/46 , B64C39/024 , B64C2201/021 , B64C2201/027 , B64C2201/042 , B64C2201/044 , B64C2201/104 , B64C2201/108 , B64C2201/146 , B64C2201/165 , G05D1/0808
摘要： An aircraft includes propellers (21, 22) at a center of the airframe (1); a first power source (23); a pitch adjuster (51-1, 51-2, 52); attitude control propellers (31-1, 31-2, 31-3, 31-4); a second power source (32-1, 32-2, 32-3, 32-4); and a control circuit (100) to control attitude of the airframe (1). The control circuit (100) includes a first yaw rotation generation control unit to control first yaw rotation generated by torques of the propellers (21, 22) with the pitch adjuster; and a second yaw rotation generation control unit to control a second yaw rotation generated by torques generated by a difference in rotation speed between the attitude control propellers (31-1, 31-2, 31-3, 31-4). The control circuit is configured to control the first yaw rotation generation control unit and the second yaw rotation generation control unit in accordance with a magnitude of a command value of yaw rotation.

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