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公开(公告)号：US12049314B2
公开(公告)日：2024-07-30
申请号：US17699312
申请日：2022-03-21
发明人： Dort Daandels , Bernhard Schlipf
摘要： An aircraft wing, including a main wing, a leading edge high lift assembly including a high lift body, and an assembly connecting the high lift body to the main wing. The high lift body is movable relative to the main wing between stowed and deployed positions. The connection assembly includes at least one rotation element mounted to the high lift body and rotatably mounted to the main wing. The main wing comprises an upper panel with a leading edge portion and a lower skin panel. The high lift body has a leading and a trailing edge. The high lift body trailing edge moves along the main wing upper skin panel leading edge portion when the high lift body is moved between the stowed and deployed positions. The upper skin panel leading edge portion is elastically deformed when the high lift body is moved from the stowed to the deployed position.
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公开(公告)号：US20240239476A1
公开(公告)日：2024-07-18
申请号：US18411179
申请日：2024-01-12
发明人： Jan HASERODT , Sarah DEHNBOSTEL
摘要： A drive assembly for driving a movable flow body of an aircraft comprises an electric motor having a two sets of independent windings, two motor control electronics units coupled with the windings and a control computer, two actuators couplable with a first or second section of the flow body, a first and a second transmission shaft, wherein the transmission shafts each have a first and a second end, wherein the electric motor is coupled with the first ends of the transmission shafts, wherein the second ends of the transmission shafts are coupled with the respective actuator, and wherein the drive assembly is designed to selectively move and hold the movable flow body into a plurality of extended positions and a retracted position relative to a fixed structural component of the aircraft by selectively moving and holding the first actuator and the second actuator.
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公开(公告)号：US20180354605A1
公开(公告)日：2018-12-13
申请号：US16002485
申请日：2018-06-07
发明人： Murray CROSS
CPC分类号： B64C3/52 , B64C13/30 , B64D45/0005 , B64D2045/0085
摘要： An aerodynamic structure is disclosed having a lifting surface, a control device and an actuation mechanism. The lifting surface has a root and a tip, and is deformable during operation of the aerodynamic structure. The control device is movably attached to the lifting surface, at or near the tip. The actuation mechanism is for controlling movement of the control device, and is configured to transmit deformation movement of the lifting surface to the control device.
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公开(公告)号：US20180099738A1
公开(公告)日：2018-04-12
申请号：US15287467
申请日：2016-10-06
CPC分类号： B64D31/04 , B64C13/30 , B64C29/0033 , G05G9/047
摘要： The present invention includes a thrust control apparatus, method and kit for a tiltrotor craft comprising a thrust control handle; a first and a second bar connected to the thrust control handle and connected to a floor support; a first end of a transverse bar connected to the first bar; a linker connected to a second end of the transverse bar; and a crankbell connected to the floor support below the first and a second bars, wherein a first end of the crankbell is connected to the linker, wherein the thrust control handle has a substantially linear motion that controls engine thrust, and the crankbell transfers the substantially linear motion of the handle into a substantially perpendicular motion that engages an engine thrust control at a second end of the crankbell.
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公开(公告)号：US09909613B2
公开(公告)日：2018-03-06
申请号：US14686413
申请日：2015-04-14
发明人： John H. Cowles, Jr. , James Beavers
CPC分类号： F16C7/02 , B64C13/30 , F16C2326/43
摘要： A compression rod has a buckling initiating feature. The compression rod includes an elongate body. The elongate body has a first cross sectional area along a first a length of the elongate body and a second cross sectional area along a second length of the elongate body. The second cross sectional area defines the buckling initiating feature. The second cross sectional area is configured to cause buckling along the elongate body upon application of a predetermined axially oriented compressive force.
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公开(公告)号：US09902487B2
公开(公告)日：2018-02-27
申请号：US15388478
申请日：2016-12-22
申请人： Area- I Inc.
发明人： Nicholas Robert Alley , Joshua Lemming Steele , Jesse Owen Williams , Daniel Kuehme , Jonathan Caleb Phillips
CPC分类号： B64C3/40 , B64C1/36 , B64C3/54 , B64C3/546 , B64C3/56 , B64C5/02 , B64C5/12 , B64C5/16 , B64C11/28 , B64C13/24 , B64C13/30 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/12 , B64C2201/123 , B64C2201/127 , B64C2211/00 , Y02T50/14 , Y02T50/44
摘要： An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.
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公开(公告)号：US20170341731A1
公开(公告)日：2017-11-30
申请号：US15166369
申请日：2016-05-27
CPC分类号： B64C9/34 , B64C5/08 , B64C5/10 , B64C9/02 , B64C9/12 , B64C9/323 , B64C13/28 , B64C13/30 , Y02T50/44
摘要： In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of a wing of an aircraft and form part of a top surface of the wing when in a first closed position, and a second deflector configured to couple to the shaft and form part of a bottom surface of the wing when in a second closed position. The first deflector and the second deflector may be configured to be positioned proximate to the tip of the wing. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.
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公开(公告)号：US20170320566A1
公开(公告)日：2017-11-09
申请号：US15584267
申请日：2017-05-02
发明人： Atra Surya GEMILANG , Marc HENCKE
摘要： Disclosed herein is an exemplary embodiment of a system for driving a slat of an aircraft. The system includes first and second hinge support elements of a wing structure, a first arm device, a second arm device, and a third arm device. Also disclosed is an aircraft having the system, an aircraft wing having the system, and a method for driving a slat of an aircraft. The system utilizes a particular configuration of connection junctions, which rotatably connect the arm devices and the hinge support elements.
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公开(公告)号：US20170297701A1
公开(公告)日：2017-10-19
申请号：US15517869
申请日：2015-10-07
CPC分类号： B64C31/06 , B64C9/20 , B64C13/16 , B64C13/30 , B64C2031/065 , F03D5/00 , F03D5/06 , F03D7/00 , F03D9/32 , F05B2240/921 , Y02E10/70 , Y02E10/728
摘要： A kite comprises: a wing; upper and lower flaps located along at least a portion of an edge of the wing that forms the trailing edge of the wing when the wing is active; a controller configured to generate control signals; and an actuator arrangement configured to change orientations of the upper and lower flaps relative to the wing based on the control signals generated by the controller.
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公开(公告)号：US20170291685A1
公开(公告)日：2017-10-12
申请号：US15388396
申请日：2016-12-22
申请人： Area- I Inc.
发明人： Nicholas Robert Alley , Joshua Lemming Steele , Jesse Owen Williams , Daniel Kuehme , Jonathan Caleb Phillips
CPC分类号： B64C3/40 , B64C1/36 , B64C3/54 , B64C3/546 , B64C3/56 , B64C5/02 , B64C5/12 , B64C5/16 , B64C11/28 , B64C13/24 , B64C13/30 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/12 , B64C2201/123 , B64C2201/127 , B64C2211/00 , Y02T50/14 , Y02T50/44
摘要： An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.
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