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1. 发明授权

US11958599B2 Supporting structure with passively adaptable profile 有权
公开(公告)号：US11958599B2
公开(公告)日：2024-04-16
申请号：US17427675
申请日：2020-02-03
申请人： Guilhem Colombiès
发明人： Guilhem Colombiès
IPC分类号： B64C3/44 , B64C3/18 , B64C3/30 , B64C3/52
CPC分类号： B64C3/44 , B64C3/182 , B64C3/30 , B64C3/52 , B64C2003/445
摘要： The invention relates to a supporting structure (46) which is positioned in a fluid flow (44) and characterised in that it is configured to be elastically deformed, on at least one portion of the supporting structure (46), between a first idle state in the absence of external stress and a second deformed state in the presence of external stresses caused by the fluid flow (44) due to a change in the orientation of the supporting structure (46) and/or the fluid flow (44). The invention also relates to an aircraft comprising at least one such supporting structure (46).

2. 发明授权

US11635772B2 Unmanned aerial vehicle with synchronized sensor network 有权
公开(公告)号：US11635772B2
公开(公告)日：2023-04-25
申请号：US16618027
申请日：2018-06-01
申请人： Romaeris Corporation
发明人： Anthony F. Pizarro , Bruno C. Doerwald
IPC分类号： G05D1/08 , B64C23/06 , B64C1/26 , B64C3/52 , B64C13/30 , B64C13/50 , B64C31/028 , B64C39/02
摘要： Disclosed is an aircraft and a method of controlling an aircraft. The aircraft comprises a continuous wing assembly extending from port to starboard sides of the aircraft. The aircraft is controlled partially by flexing portions of the wing, and partially or totally by mechanical systems that alter the position of a fuselage with respect to the wing. The fuselage is attached to the wing by a wing/fuselage joint structure that permits at least two mutually orthogonal axes of rotation of the fuselage relative to the wing. The aircraft includes a sensors, a telemetry system linked to a remote server, and a control system for programming flight information and aircraft control instructions and a plurality of actuators responsive to the control system for rotating the fuselage relative to the wing and flexing the wing for controlling the flight of the aircraft in response to instructions from the control system.

3. 发明授权

US11008087B2 Wing-twist controlled aircraft 有权
公开(公告)号：US11008087B2
公开(公告)日：2021-05-18
申请号：US15702441
申请日：2017-09-12
申请人： Facebook, Inc.
发明人： Daniel Uhlig , Cory A. Kays , Kevin Uleck , Gilbert L. Crouse, Jr.
IPC分类号： B64C3/52 , B64C39/04
摘要： The present disclosure directed to an aircraft comprising one or more propulsion devices, a flexible wing, at least two tail booms having a proximal end and a distal end, the tail booms being secured to said flexible wing at the proximal end, wherein the tail booms comprise of a tail section connected at the distal end of said tail boom and wherein the tail section comprises of at least one control surface.

4. 发明申请

US20200086972A1 METHOD FOR CONTROLLING AN AIRCRAFT, AND AN AIRCRAFT (VARIANTS) 审中-公开
公开(公告)号：US20200086972A1
公开(公告)日：2020-03-19
申请号：US16133227
申请日：2018-09-17
申请人： UAVOS Holdings Limited
发明人： Tsimafei BATURA , Yury TYTSYK , Aliaksei STRATSILATAU , Viachaslau SHIPILEUSKI
IPC分类号： B64C3/38 , B64C39/04 , B64C3/52
摘要： A multi-boom aircraft with an adjustable wing geometric twist includes at least one wing, and at least three booms arranged transversely to at least one of the wings. Each of the booms includes at least one actuator, and the at least one wing is mounted on the booms so as at least a portion of the corresponding wing can be pivoted by means of the actuators about an axis extending substantially along the corresponding wing.

5. 发明申请

US20190127043A1 WING SEGMENT AND AIRCRAFT HAVING A WING SEGMENT 审中-公开
公开(公告)号：US20190127043A1
公开(公告)日：2019-05-02
申请号：US16160171
申请日：2018-10-15
申请人： Airbus Operations GmbH
发明人： LARS KROG , PASQUALE BASSO
IPC分类号： B64C3/52 , B64C3/14 , B64C3/26 , B64C23/00
摘要： A wing segment for an aircraft includes a first skin element with a material having anisotropic characteristics and a rib element arranged between leading and trailing edges of the wing segment. The first skin element is attached to the rib element such that deformation of the skin element results in a twist of the wing segment with respect to a main extension direction of the wing segment. The wing segment further includes a control unit to control deformation of the skin element in order to adjust the twist of the wing segment to achieve a predetermined twist of the wing segment.

6. 发明授权

US09856012B2 Morphing wing for an aircraft 有权
公开(公告)号：US09856012B2
公开(公告)日：2018-01-02
申请号：US14408722
申请日：2013-06-21
申请人： BOMBARDIER INC.
发明人： Fengfeng Xi , Allan Daniel Finistauri , Amin Moosavian
IPC分类号： B64C3/38 , B64C3/44 , B64C3/54 , B64C3/52 , B64C3/40
CPC分类号： B64C3/38 , B64C3/385 , B64C3/40 , B64C3/44 , B64C3/52 , B64C3/54 , B64C2003/445 , B64C2003/543 , Y02T50/14
摘要： A morphing wing for an aircraft includes first and second structural ribs with four active members and four passive members connected therebetween. First and second active members and third and fourth active members attach at first and second positions. The first and third active members and the second and fourth active members attach at third and fourth positions. A first passive member connects between third and fifth positions. A second passive member connects between second and seventh positions. A third passive member connects between fourth and sixth positions. A fourth passive member connects between first and eighth positions. Adjustment of the four active members morphs the wing from a first configuration to a second configuration. The first and second positions are at corners of a first quadrilateral diagonally opposite to one another. The four passive members attach to the first structural rib at the corners of the first quadrilateral.

7. 发明授权

US09764819B2 Active dihedral control system for a torsionally flexible wing 有权
公开(公告)号：US09764819B2
公开(公告)日：2017-09-19
申请号：US14838297
申请日：2015-08-27
申请人： AeroVironment Inc.
发明人： Greg T. Kendall , Derek L. Lisoski , Walter R. Morgan , John A. Griecci
IPC分类号： B64C3/38 , B64C3/42 , B64C3/52 , B64C15/02 , B64C17/00 , B64C39/02 , B64C39/10 , B64D27/24 , B64D31/06 , H04B7/185
CPC分类号： B64C3/38 , B64C3/42 , B64C3/52 , B64C15/02 , B64C17/00 , B64C39/024 , B64C39/10 , B64C2201/028 , B64C2201/042 , B64C2201/102 , B64C2201/122 , B64C2201/126 , B64C2201/127 , B64C2201/146 , B64C2201/165 , B64D27/24 , B64D31/06 , B64D2211/00 , H04B7/18504 , Y02T50/12 , Y02T50/14 , Y02T50/44 , Y02T50/55
摘要： A span-loaded, highly flexible flying wing, having horizontal control surfaces mounted aft of the wing on extended beams to form local pitch-control devices. Each of five spanwise wing segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other wing segments, to minimize inter-segment loads. Wing dihedral is controlled by separately controlling the local pitch-control devices consisting of a control surface on a boom, such that inboard and outboard wing segment pitch changes relative to each other, and thus relative inboard and outboard lift is varied.

8. 发明申请

US20170015427A1 SYSTEMS AND METHODS FOR APPLYING DEFORMATIONS TO A STRUCTURAL SURFACE 审中-公开
标题翻译：将变形应用于结构表面的系统和方法
公开(公告)号：US20170015427A1
公开(公告)日：2017-01-19
申请号：US15208713
申请日：2016-07-13
申请人： AerolceFree Ltd.
发明人： Amihay Gornik
IPC分类号： B64D15/16 , B64C3/52 , B64D15/22
CPC分类号： B64D15/16
摘要： System for applying deformations to a structural surface, the system may include an actuating unit, operable to produce a periodically variable force which is applied to at least one first location of the structural surface, thereby displacing the structural surface in a plurality of directions at the at least one first location and a passive displacing unit comprising a weight and a displacer supporting the weight and fixed to at least one second location on the structural surface; wherein the structural surface is capable of transferring vibrations between the at least one first location and the at least one second location, so that the displacing of the structural surface at the at least one first location produces forces which are applied to the weight via the structural surface and the displacer, bringing the weight to resonance, thereby displacing the structural surface in a plurality of directions at each of the at least one second location.
摘要翻译：用于将变形施加到结构表面的系统，系统可以包括致动单元，其可操作以产生施加到结构表面的至少一个第一位置的周期性可变的力，从而在结构表面的多个方向上移动结构表面至少一个第一位置和被动移位单元，其包括重物和支撑所述重物并且固定到所述结构表面上的至少一个第二位置的置换器; 其中所述结构表面能够在所述至少一个第一位置和所述至少一个第二位置之间传递振动，使得所述结构表面在所述至少一个第一位置处的位移产生通过所述结构施加到所述重物的力表面和置换器，使重量共振，从而在至少一个第二位置的每一个处沿着多个方向移位结构表面。

9. 发明授权

US09481450B2 Active strut apparatus for use with aircraft and related methods 有权
标题翻译：用于飞机和相关方法的主动支柱装置
公开(公告)号：US09481450B2
公开(公告)日：2016-11-01
申请号：US14321428
申请日：2014-07-01
申请人： The Boeing Company
发明人： Dale M. Pitt , Darin P. Haudrich
IPC分类号： B64C3/38 , B64C13/28 , B64C3/52 , B64C3/16
CPC分类号： B64C13/28 , B64C3/16 , B64C3/52 , Y02T50/12 , Y02T50/14 , Y02T50/44
摘要： Active strut apparatus for use with aircraft and related methods are disclosed. An example apparatus includes a first strut having a first end and a second end opposite the first end, the first end of the first strut is operatively coupled to a fuselage of an aircraft and the second end of the first strut is operatively coupled to a wing of the aircraft, and a first actuator is operatively coupled to the first strut to change an effective length of the first strut.
摘要翻译：公开了用于飞机和相关方法的主动支柱装置。示例性装置包括具有第一端和与第一端相对的第二端的第一支柱，第一支柱的第一端可操作地联接到飞行器的机身，并且第一支柱的第二端可操作地联接到翼并且第一致动器可操作地联接到第一支柱以改变第一支柱的有效长度。

10. 发明授权

US08695925B2 Elastically deformable side-edge link for trailing-edge flap aeroacoustic noise reduction 有权
标题翻译：弹性变形侧边缘连接，用于后缘翼片气动噪声降低
公开(公告)号：US08695925B2
公开(公告)日：2014-04-15
申请号：US13326779
申请日：2011-12-15
申请人： Mehdi R. Khorrami , David P. Lockard , James B. Moore , Ji Su , Travis L. Turner , John C. Lin , Karen M. Taminger , Seun K. Kahng , Scott A. Verden
发明人： Mehdi R. Khorrami , David P. Lockard , James B. Moore , Ji Su , Travis L. Turner , John C. Lin , Karen M. Taminger , Seun K. Kahng , Scott A. Verden
IPC分类号： B64C9/00 , B64C5/10 , B64C3/52
CPC分类号： B64C9/16 , B64C9/02 , Y02T50/32 , Y02T50/44
摘要： A system is provided for reducing aeroacoustic noise generated by an aircraft having wings equipped with trailing-edge flaps. The system includes a plurality of elastically deformable structures. Each structure is coupled to and along one of the side edges of one of the trailing-edge flaps, and is coupled to a portion of one of the wings that is adjacent to the one of the side edges. The structures elastically deform when the trailing-edge flaps are deployed away from the wings.
摘要翻译：提供了一种用于减少由具有后缘翼片的翼的飞行器产生的航空声学噪声的系统。该系统包括多个可弹性变形的结构。每个结构联接到并沿着一个后缘翼片的一个侧边缘，并且联接到与一个侧边缘相邻的翼中的一个的一部分。当后缘襟翼远离翼片时，结构弹性变形。

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