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公开(公告)号：US12071221B2
公开(公告)日：2024-08-27
申请号：US17838377
申请日：2022-06-13
发明人： Benjamin Bishop
摘要： A spoiler actuation apparatus for moving an aircraft spoiler. The spoiler is moveable between a stowed configuration and a deployed configuration. The spoiler actuation apparatus includes a guide member, a rack mounted on the guide member and slideable along a longitudinal axis of the guide member, and a gear coupled to the rack, the gear arranged to move the spoiler in response to sliding of the rack. The rack is held at a first position when the spoiler is in the stowed configuration. An actuator moves the rack from the first position to a second position along the longitudinal axis. When the rack is at the second position, the rack is operable to accelerate relative to the guide member away from the second position by an aerodynamic force acting on the spoiler.
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公开(公告)号：US20230406481A1
公开(公告)日：2023-12-21
申请号：US18333964
申请日：2023-06-13
发明人： Stefan BENSMANN , Martin FEES
摘要： A support arrangement for a leading-edge high lift device comprising a support arm for movably supporting the leading-edge high lift device on a wing structure. In order to accommodate the supply of the leading-edge high lift device with a fluid such as an anti-ice fluid, for example pressurized hot air, the support arm is configured as a fluid conduit for feeding fluid to and/or from the leading-edge high lift device. The leading-edge high lift device may be configured as a droop nose device.
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公开(公告)号：US11845550B2
公开(公告)日：2023-12-19
申请号：US17433944
申请日：2020-02-28
发明人： Stefan Bensmann , Marcus Erban , Martin Fees
CPC分类号： B64C9/22 , B64C9/08 , B64C3/185 , B64C2009/143
摘要： A wing leading-edge device is disclosed having a slat body having a front side with a forward skin and a back side with a rearward skin, and at least a drive arrangement having at least one lug and a slat track, wherein the back side extends between an upper spanwise edge of the forward skin and a lower spanwise edge of the forward skin. The back side is defined by a continuously curved profile contour for receiving a fixed leading edge, and the at least one lug is at least partially arranged between the back side and the front side. The slat track is coupled with the first lug. The connection points to the slat body are shifted far forward to improve the load introduction and reduce moments acting on the drive mechanism.
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公开(公告)号：US20230002031A1
公开(公告)日：2023-01-05
申请号：US17779933
申请日：2020-11-03
发明人： Stefan BENSMANN
摘要： A wing (5) including a fixed wing (7), a high-lift device (15) and a hold-down arrangement arranged (27) between two supports (23, 25) of the high lift device (15) having a first hold-down element (29) attached to the high-lift device (15) and a second hold-down element (31) attached to the fixed wing (7). The first hold-down element (29) contacts the second hold-down element (31) when the high-lift device (15) is in a retracted position in which it prevents a trailing edge (22) of the high-lift device (15) from detaching from an upper surface (19) of the fixed wing (7) when the fixed wing (7) deforms in the spanwise direction. One of the hold-down elements (29, 31) is a load-limited hold-down element (32) which transition from a first stable state to a second state when the load acting on the hold-down arrangement (27) exceeds an operational threshold.
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公开(公告)号：US11433988B2
公开(公告)日：2022-09-06
申请号：US17057948
申请日：2019-05-24
申请人： SONACA S.A.
发明人： Xavier Godfroid
摘要： An aircraft wing including a mobile leading edge flap associated with a guiding device arranged at the front of a front spar of a wing box, and including: —a pivoting member having one end connected to the spar by an articulated linkage; —a pivoting member connected to one end of the member by an articulated linkage, the end of this member being connected to the flap via an articulated linkage; —a guide rail receiving a tracking member supported by the member, the rail defining a path inscribed on the surface of an imaginary sphere, the centre of which corresponds to a point of convergence of the axes of the three linkages.
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公开(公告)号：US20220135206A1
公开(公告)日：2022-05-05
申请号：US17433944
申请日：2020-02-28
发明人： Stefan BENSMANN , Marcus ERBAN , Martin FEES
摘要： A wing leading-edge device is disclosed having a slat body having a front side with a forward skin and a back side with a rearward skin, and at least a drive arrangement having at least one lug and a slat track, wherein the back side extends between an upper spanwise edge of the forward skin and a lower spanwise edge of the forward skin. The back side is defined by a continuously curved profile contour for receiving a fixed leading edge, and the at least one lug is at least partially arranged between the back side and the front side. The slat track is coupled with the first lug. The connection points to the slat body are shifted far forward to improve the load introduction and reduce moments acting on the drive mechanism.
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公开(公告)号：US11104423B2
公开(公告)日：2021-08-31
申请号：US16209244
申请日：2018-12-04
发明人： Dietmar Döring
摘要： A wing (5) for an aircraft (1) and include a fixed wing (7), a high lift system (9) including a high lift surface (27) movably mounted to the fixed wing (7), and a high lift actuation system (29) for moving the high lift surface (27) relative to the fixed wing (7) between a retracted position and at least one deployed position, a foldable wing tip portion (11) mounted to the fixed wing (7) pivotally about an axis of rotation (35) between an extended position and a folded position, a tip actuation unit (13) for moving the foldable wing tip portion (11) between the extended position and the folded position. The object to provide a simple, cost-efficient and light-weight wing, is achieved in that the high lift actuation system (29) is drivingly coupled to the tip actuation unit (13) to provide power to the tip actuation unit (13)
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公开(公告)号：US20200307760A1
公开(公告)日：2020-10-01
申请号：US16823837
申请日：2020-03-19
申请人： EMBRAER S.A.
发明人： Andre Ganam de QUEIROZ , Alexandre Takao MOTOYAMA , Azelio PASQUINI , Douglas Carrari FIRMINO , Egon dos SANTOS BORGES , Henrique Fonseca de ARAUJO , Luiz Flavio FERNANDES , Nilson Luiz DAVID
摘要： An aircraft wing is provided with a shutter mechanism to close a cut-out opening in the leading edge of the wing when a leading edge wing slat associated with the wing leading edge is moved to a deployed condition.
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公开(公告)号：US20200277039A1
公开(公告)日：2020-09-03
申请号：US16796025
申请日：2020-02-20
发明人： Stefan Bensmann , Marcus Erban , Martin Fees
摘要： A wing leading edge device includes a flow body having a front side, which is delimited by a first spanwise edge and a second spanwise edge, a back side, which is delimited by the first spanwise edge and the second spanwise edge, a front skin arranged on the front side, a back skin arranged on the back side, and at least one stiffening arrangement between the front skin and the back skin in the region of the first spanwise edge, wherein the front skin extends continuously and free from interruptions between the first spanwise edge and the second spanwise edge and covers the at least one stiffening arrangement.
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公开(公告)号：US10647444B2
公开(公告)日：2020-05-12
申请号：US15851805
申请日：2017-12-22
发明人： Mark Hubberstey , Mark Timms
IPC分类号： B64D45/00 , B64C13/28 , B64C9/22 , B64F5/40 , G07C5/08 , B64D15/12 , B64C3/00 , B64C9/24 , B64F5/10
摘要： An actuator failure or disconnection detection device for an aircraft leading edge slat comprises a base and a biasing assembly mounted to the base and movable relative thereto. The base and biasing assembly are removably mountable between a fixed structure in the aircraft wing and the slat at an actuator location. The device further comprises an indicator for indicating the amount of movement of the biasing assembly in a direction towards the base when the slat is retracted towards the wing leading edge. The indicator may be a collar slidably mounted on the device.
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