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公开(公告)号：US11945566B2
公开(公告)日：2024-04-02
申请号：US17851189
申请日：2022-06-28
发明人： Tim Lübbert , Michael Rempe , Frank Schneider
CPC分类号： B64C1/1453 , F16L53/38 , H05B3/48
摘要： A drain mast for an aircraft for discharge of water from the aircraft interior with a line which extends in a line direction from a connector end to a discharge end. The connector end can connect to another line in the interior of the aircraft, through which further line water flows into the drain mast. The discharge end can discharge water into a surrounding area of the aircraft. The line includes a plastic, into which a conductive material is embedded, by which the line can be heated electrically, by a heating current being conducted through the conductive material. A proportion of the embedded conductive material in the line increases in the line direction per length unit from the connector end of the line towards the discharge end such that the heating power which is introduced into the line per length unit increases from the connector end towards the discharge end.
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公开(公告)号：US20240101246A1
公开(公告)日：2024-03-28
申请号：US18471719
申请日：2023-09-21
发明人： Bernhard SCHLIPF , Dennis KREY
CPC分类号： B64C9/18 , B64C9/02 , B64C13/38 , F16F15/02 , F16F2228/066
摘要： A wing component for an aircraft, comprising a leading edge part and a trailing edge part pivotably mounted to the leading edge part so as to pivot about a pivot axis, an actuator unit configured for moving the trailing edge part relative to the leading edge part, and a damper device configured for damping uncontrolled movement between the leading edge part and the trailing edge part. The trailing edge part comprises a first part portion and a second part portion arranged next to each other in a span direction and configured to pivot about the pivot axis individually, the damper device comprises a damping element coupled between the first part portion and the second part portion to damp relative movement of the first part portion and the second part portion.
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公开(公告)号：US20240093711A1
公开(公告)日：2024-03-21
申请号：US18460896
申请日：2023-09-05
发明人： Jörn SKIRKE
CPC分类号： F16B19/1036 , F16B19/008
摘要： A blind rivet, for connecting workpieces, comprising a hollow, deformable rivet body with a bearing collar and a sleeve attached thereto, a rivet mandrel in the sleeve and extending through the bearing collar, having a tool holder head, and a sealing ring. The sealing ring is arranged between the bearing collar and the tool holder head and is made of a curable and not fully cured sealing material. During contraction of the blind rivet, the sealing ring is pressed axially towards the bearing collar by a tool that can be connected to the tool holder head or by a section of the rivet mandrel. The sealing ring is designed to flow radially and axially into gaps and spaces on the bearing collar and between the bearing collar and the workpieces while the sealing ring is compressed, and to adhere there.
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公开(公告)号：US11932388B2
公开(公告)日：2024-03-19
申请号：US17581640
申请日：2022-01-21
发明人： Ivano Bertolini , Stefano Giaquinto , Sebastian Welz , Nina Düren , Jeff Wee Hong Yap , Michael Höft , Nicole Jordan , Frank Nielsen
摘要： A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) with a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing a plenum (7), an outer wall element (23) facing ambient flow (25), and a core assembly (97). The outer wall element (23) includes micro pores (31) and the inner wall element (21) includes openings (33) which form a fluid connection from ambient flow, through the core assembly (97) and to the plenum (7). The thickness of the outer wall element is reduced due to the first attachment end (17) and/or at the second attachment end (19) attached to the inner wall element (21) by both bonding and fasteners (85, 87, 89, 91).
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公开(公告)号：US11926406B2
公开(公告)日：2024-03-12
申请号：US17747184
申请日：2022-05-18
发明人： Sören Ohle
CPC分类号： B64C1/1415 , B64C1/1423 , B64C1/1461 , E05B15/024 , E05B85/24
摘要： A hatch locking device for an aircraft hatch includes an eccentric bush which can be connected to a hatch bulkhead of the aircraft hatch panel, an inner lining which is introduced into the eccentric bush and has a bolt receptacle which is oriented centrally along a bolt receptacle axis for receiving a locking bolt, a conical pressing sleeve in the inner lining, a conical clamping sleeve, the outer conical shell face of which is in displaceable engagement with an inner conical shell face of the conical pressing sleeve, and the inner cylindrical shell face of which is flush with the outer wall of the bolt receptacle, and linear actuators which are mounted on in each case two opposite sides of the conical pressing sleeve in the inner lining and are designed to displace the conical pressing sleeve along the bolt receptacle axis with respect to the conical clamping sleeve.
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公开(公告)号：US11919619B2
公开(公告)日：2024-03-05
申请号：US16509748
申请日：2019-07-12
发明人： Claus-Peter Gross
CPC分类号： B64C1/18 , B64D11/0023 , B64D2011/0046
摘要： An aircraft-floor element comprising a first cladding element configure to be swung from a first position to a second position. In the first position, the first cladding element is arranged parallel to a main plane of the aircraft-floor element and on a side of the aircraft-floor element which is directed towards a passenger cabin. In the second position, the first cladding is arranged at an angle to the main plane of the aircraft-floor element, wherein it forms a cladding for a cargo space. An aircraft zone having an aircraft-floor element and an aircraft having such an aircraft zone are also disclosed.
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公开(公告)号：US20240051667A1
公开(公告)日：2024-02-15
申请号：US18364655
申请日：2023-08-03
发明人： Hermann BENTHIEN , Andreas POPPE
IPC分类号： B64D11/06
CPC分类号： B64D11/0696
摘要： A rail system for the installation of objects in a cabin of a vehicle having a base rail, an installation rail, and connecting devices for connecting the base rail and the installation rail to one another in a mutually parallel orientation. The base rail has a bottom side, with a securing portion for securing the base rail on a structural component of the vehicle, and a top side. The installation rail has an installation surface on which the objects can be mounted and connected to the installation rail. The rail system is configured to position the installation surface with a predetermined spacing to the top side such that at least one lateral intermediate space is formed between the installation surface and the base rail for the purposes of form-fittingly holding a floor panel.
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公开(公告)号：US20240018806A1
公开(公告)日：2024-01-18
申请号：US18221952
申请日：2023-07-14
发明人： Florian Müller , Jan-Luca Hünting
CPC分类号： E05B85/00 , B64D11/00 , E05B81/06 , E05B81/08 , E05B81/18 , E05B81/70 , E05B83/00 , B64D2231/025
摘要： A device for latching a door of an oxygen mask container in an aircraft cabin includes a door for an oxygen mask container having an inner side, outer side and hinge, a first latching device attached to the inner side, and a second latching device movable relative to the first latching device to selectively engage or disengage the second latching device. A retaining element is attachable to a structural part inside the oxygen mask container. A test control device on the inner side of the door includes a movable hook element and can move the hook element to a first or second position. The hook element can engage the retaining element in the first position to restrict an opening degree of the door. The hook element is placed in the second position such that when the door is opened, the hook element is moved past the retaining element.
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公开(公告)号：US20240017817A1
公开(公告)日：2024-01-18
申请号：US18346989
申请日：2023-07-05
发明人： Stefan Bensmann
摘要： A wing for an aircraft includes a leading edge, a trailing edge, an upper skin extending between the leading edge and the trailing edge, a lower skin extending between the leading edge and the trailing edge, at least one spar extending between the upper skin and the lower skin in a spanwise direction to create a wing box with the upper skin and the lower skin, and at least one droop nose at the leading edge, wherein the at least one droop nose is coupled with a forward end of a hinge arm that extends in a chordwise direction, and wherein a rearward end of the hinge arm is swivably supported directly at or in the wing box.
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公开(公告)号：US11866170B2
公开(公告)日：2024-01-09
申请号：US17615068
申请日：2020-07-07
发明人： Stefan Bensmann , Marcus Erban , Martin Fees
摘要： A movable flow body device for an aircraft including an elongated flow body having a main extension axis, a first mechanical interface in a first position along the main extension axis, a second mechanical interface in a second position and a third mechanical interface in a third position. The first mechanical interface may be a master interface arranged in a central region, while the second and third mechanical interfaces are slave interfaces. Preferably, in the outboard position, a link plate between a support lever and a support rib of the flow body is inverted compared to the further inboard mechanical interface, which allows for supporting slimmer and longer flow bodies in the outboard region and providing a rigging hinge line through the whole flow body.
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