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公开(公告)号：US11273902B2
公开(公告)日：2022-03-15
申请号：US16297126
申请日：2019-03-08
发明人： Alvin Gatto
摘要： A blade or wing element includes a plurality of ribs (20) rotatable and/or slidable with respect to one another whereby to vary the aerodynamic configuration of the blade or wing element by causing a twist thereof. A blade or wing or blade or wing assembly, including such a blade or wing element is disclosed, as well as an aerodynamic apparatus such as an aircraft, or a wind turbine. A method of assembling a blade or wing element is also disclosed.
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82.发明授权公开(公告)号：US11111004B2
公开(公告)日：2021-09-07
申请号：US16555221
申请日：2019-08-29
发明人： Robert Cheikh Sarraf
摘要： A device to fasten a system to a structure of a vehicle includes a drive unit that provides rotary movement of a drive element relative to the structure. The device has first and second supporting elements. The first supporting element is rotatably coupled to the drive element via a first rotation axis, and is rotatably mounted to the structure via a second rotation axis. The second supporting element is rotatably coupled to the first supporting element, and a first connecting element, which is rotatably mounted to the structure via a third rotation axis. The first connecting element is rotatably coupled to the second supporting element via a fourth rotation axis. The second supporting element is rotatably coupled to the first supporting element via a fifth rotation axis. During movement, the first supporting element has a different rotational speed than the second supporting element.
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公开(公告)号：US11110647B2
公开(公告)日：2021-09-07
申请号：US15963890
申请日：2018-04-26
申请人： The Boeing Company
IPC分类号： B29C61/06 , B64C3/48 , B64C3/52 , B29C70/88 , B29B11/16 , B29C70/32 , B29C70/22 , B29C70/30 , B32B15/08 , F03G7/06 , H05K1/05 , H05K1/16 , B64C3/44 , B64C27/72 , B64C3/54 , B29C53/82 , B29K71/00 , B29K267/00 , B29L31/30
摘要： Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.
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公开(公告)号：US20210261234A1
公开(公告)日：2021-08-26
申请号：US17174571
申请日：2021-02-12
申请人： AeroVironment, Inc.
IPC分类号： B64C3/56 , B64C13/34 , B64C3/44 , B64C3/50 , B64C5/12 , B64C13/18 , B64C9/36 , B64C39/02 , B64C9/02 , B64C9/08 , B64C9/18 , B64C11/00
摘要： A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.
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公开(公告)号：US10710702B2
公开(公告)日：2020-07-14
申请号：US15674919
申请日：2017-08-11
发明人： Edward Davis
摘要： An apparatus and method are provided for a shape adaptive airfoil configured to be coupled with a tip of an airplane wing. In one embodiment, the shape adaptive airfoil is a blended winglet comprised of a base section coupled with the airplane wing, a blade section projecting in a vertical direction above the base section, and a radius section interconnecting the base and blade sections. Adaptive control structures may be incorporated into leading and trailing edges of the base section and the blade section. The adaptive control structures of the base section may facilitate changing a camber profile of the shape adaptive airfoil. The adaptive control structures of the blade section may enable changes to a toe angle of the blade section.
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公开(公告)号：US10549838B2
公开(公告)日：2020-02-04
申请号：US15452993
申请日：2017-03-08
申请人： The Boeing Company
摘要： Flexible control surfaces and related methods are disclosed. Example apparatus disclosed herein include an airfoil including a skin, the skin having perforations filled with an elastomer to increase a flexibility of the skin; and a flexible core adjacent the perforations of the skin to support the skin.
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公开(公告)号：US10543897B2
公开(公告)日：2020-01-28
申请号：US15477986
申请日：2017-04-03
申请人： The Boeing Company
IPC分类号： B64C3/18 , C22F1/10 , F03G7/06 , B21C37/04 , B64C1/06 , C22F1/00 , B64C3/44 , B64C27/473 , B64C27/72 , B64C1/00
摘要： There is provided a training system capable of performing work. The system has a shape memory alloy (SMA) actuator exhibiting a generally planar transformational behavior. The system further has one or more heating elements for transforming the SMA actuator from an original shape to a trained shape, thereby performing work.
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88.发明授权公开(公告)号：US10513346B2
公开(公告)日：2019-12-24
申请号：US15735307
申请日：2016-06-07
申请人： BOMBARDIER INC.
发明人： Benoit Ouellette
摘要： Systems, devices and methods a for use with one or more high-lift flight control surfaces (24) of aircraft are disclosed. One exemplary method comprises receiving data representative of a commanded configuration (48) for a high-lift flight control surface (24); and on a display device (14) of the aircraft, showing an indicator (30) indicating the commanded configuration and a corresponding commanded position (50) for the high-lift flight control surface (24). The indicator (30) graphically indicates a correlation between the commanded configuration (48) and the corresponding commanded position (50) for the high-lift flight control surface (24).
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公开(公告)号：US10479478B2
公开(公告)日：2019-11-19
申请号：US13989453
申请日：2013-03-28
发明人： Mohammed Azad Hussain , Anthony Machell , Paul Robinson , Henry Alexander Maples , Charnwit Tridech , Alexander Bismarck
IPC分类号： B64C3/38 , B64C3/48 , B64C3/20 , B29C70/08 , B29C70/20 , B29C61/00 , C08L33/26 , C08L63/00 , B64C3/44
摘要： A morphing skin for an air vehicle structure, the skin being formed by a composite material which includes: a multiplicity of fibers, a matrix incorporating the fibers, and a thermo-sensitive material, such as a thermo-plastic. The thermo-sensitive material can be reversibly transitionable in response to a change in temperature, between (i) an ambient temperature mode in which the thermo-sensitive material is capable of transferring loads in the composite material, and (ii) a heated mode in which the ability of the thermo-sensitive material to transfer the loads is reduced. This can allow the stiffness of the skin to be temporarily reduced to enable the skin to be morphed into a different shape.
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公开(公告)号：US10464667B2
公开(公告)日：2019-11-05
申请号：US15280961
申请日：2016-09-29
申请人： Ampaire, Inc.
发明人： Cory Michael Combs
摘要： An oblique rotor-wing aircraft may be capable of vertical take-off and landing, subsonic cruise, transonic cruise, and/or supersonic cruise. The oblique rotor-wing aircraft may comprise one or more of a fuselage, a rotor-wing, a thrust-vectored propulsion system, a locking mechanism, and/or other components. The rotor-wing may be rotatably coupled to the fuselage. The rotor-wing may rotate about an axis in a first flight mode for vertical takeoff and landing. The oblique rotor-wing aircraft may include a thrust-vectored propulsion system that drives the rotation of the rotor-wing about the axis. The thrust-vectored propulsion system may include multiple, separately operable propulsion systems coupled to the rotor-wing and/or the fuselage. The oblique rotor-wing aircraft may comprise a locking mechanism that locks the rotor-wing at an angle oblique to the fuselage responsive to initiation of a second flight mode. The rotor-wing may be fixed at an angle oblique to the fuselage during the second flight mode.
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