专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 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.

2. 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）。

3. 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.

4. 发明公开

EP4414261A1 AIRCRAFT 审中-公开
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.

6. 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.

7. 发明公开

EP3344534A1 UNIVERSAL VEHICLE WITH IMPROVED STABILITY FOR SAFE OPERATION IN AIR, WATER AND TERRAIN ENVIRONMENTS 有权
公开(公告)号：EP3344534A1
公开(公告)日：2018-07-11
申请号：EP16842803.5
申请日：2016-08-30
申请人： University of Maryland, College Park
发明人： VALENTE, Evandro Gurgel do Amaral , WERELEY, Norman, M. , VALENTE, Eduardo Gurgel do, Amaral
IPC分类号： B64C3/14 , B64C29/00
CPC分类号： B64C37/00 , B64C5/02 , B64C11/46 , B64C15/12 , B64C19/00 , B64C29/0033 , B64C29/02 , B64C39/024 , B64C39/10 , B64C2201/028 , B64C2201/088 , B64C2201/208 , B64C2211/00 , B64D29/00
摘要： The universal vehicle system is designed with a lifting body which is composed of a plurality of interconnected modules which are configured to form an aerodynamically viable contour of the lifting body which including a front central module, a rear module, and thrust vectoring modules displaceably connected to the front central module and operatively coupled to respective propulsive mechanisms. The thrust vectoring modules are controlled for dynamical displacement relative to the lifting body (in tilting and/or translating fashion) to direct and actuate the propulsive mechanism(s) as needed for safe and stable operation in various modes of operation and transitioning therebetween in air, water and terrain environments.

8. 发明公开

EP4400932A1 METHOD OF OPERATING AN AERIAL VEHICLE AND CONTROLLER 审中-公开
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.

9. 发明公开

EP4375496A2 VANE ASSEMBLY FOR AN UNDUCTED THRUST PRODUCING SYSTEM 审中-公开
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.

10. 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.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式