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公开(公告)号：US11524764B2
公开(公告)日：2022-12-13
申请号：US17239577
申请日：2021-04-24
Applicant: The Boeing Company
Inventor： Steve G. Mackin , Lowell B. Campbell
Abstract: An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to move the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is moved away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.
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公开(公告)号：US11312475B2
公开(公告)日：2022-04-26
申请号：US16711488
申请日：2019-12-12
Applicant: GOODRICH ACTUATION SYSTEMS SAS
Inventor： Raphael Medina
Abstract: A system for detecting and controlling the position of a spoiler of an aircraft wing is described herein comprising: a hydraulic actuator having a piston rod operably connected to the spoiler, the piston rod being moveable between a retracted position, a neutral position and an extended position; and means for providing power to said hydraulic actuator; and a mechanical device for detecting whether the piston rod is in the retracted position, the neutral position or the extended position; and means, operatively connected to the mechanical device, that is configured to provide a change in a load applied to said hydraulic actuator, wherein said means is configured to change said load based on whether said piston rod is detected as being in said retracted position or said extended position.
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公开(公告)号：US11260959B2
公开(公告)日：2022-03-01
申请号：US16513340
申请日：2019-07-16
Applicant: Gulfstream Aerospace Corporation
Inventor： Thomas Landers , Michael Malluck
Abstract: Aircraft, auto speed brake control systems, and methods for controlling drag of an aircraft are provided. In one example, an aircraft includes an aircraft structure. A drag device is operatively coupled to the aircraft structure between a stowed and a deployed position and/or an intermediate deployed position. A speed brake controller is in communication with the drag device to control movement. An autothrottle-autospeedbrake controller is in communication with the speed brake controller and is configured to receive data signals. The autothrottle-autospeedbrake controller is operative to direct the speed brake controller to control movement of the drag device between the stowed position and the deployed position and/or the intermediate deployed position in response to at least one of the data signals.
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公开(公告)号：US11072415B2
公开(公告)日：2021-07-27
申请号：US16111379
申请日：2018-08-24
Applicant: SPIRIT AEROSYSTEMS, INC.
Inventor： Randall Ray West
Abstract: An aircraft engine nacelle spoiler assembly including a number of spoilers and actuators. Each spoiler has a drag surface and a nacelle connection point. The spoilers are shiftable via the actuators between a stowed position and a deployed position such that the drag surfaces are substantially parallel with the direction of relative wind when the spoilers are stowed and exposed to the relative wind when the spoilers are deployed.
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公开(公告)号：US11014646B2
公开(公告)日：2021-05-25
申请号：US16278450
申请日：2019-02-18
Applicant: The Boeing Company
Inventor： Steve G. Mackin , Lowell B. Campbell
Abstract: An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The panel trailing edge portion is pivotably coupled to a vehicle body. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to pivot the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is pivoted away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.
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Patent Agency Ranking
公开(公告)号：US20200262540A1
公开(公告)日：2020-08-20
申请号：US16278450
申请日：2019-02-18
Applicant: The Boeing Company
Inventor： Steve G. Mackin , Lowell B. Campbell
IPC: B64C9/32
Abstract: An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The panel trailing edge portion is pivotably coupled to a vehicle body. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to pivot the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is pivoted away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.
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公开(公告)号：US20200207483A1
公开(公告)日：2020-07-02
申请号：US16623487
申请日：2018-07-08
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Ido Meidad
Abstract: Computerized system and method of controlling a refueling device including, when the device is in a non-engaged state: receiving a first roll angle of a tanker, determining a first desired roll angle, and providing a command for controlling a roll element, thereby attempting to achieve or maintain a first roll angle that is substantially the same as the roll angle of the tanker. And, when the device is in an engaged state: receiving a second roll angle of the tanker, determining a second desired roll angle, and providing a command related to the desired roll angle for controlling a yaw element, thereby attempting to achieve or maintain a second roll angle that is substantially the same as the roll angle of the tanker, wherein the roll angle of the device during the engaged state is facilitated due to a degree of freedom between the refueling device body and refueling nozzle.
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公开(公告)号：US20200180749A1
公开(公告)日：2020-06-11
申请号：US16216769
申请日：2018-12-11
Applicant: THE BOEING COMPANY
Inventor： Kevin Tsai , Donald Drew Reinhart
Abstract: A spoiler mechanism for an aircraft includes a spoiler fore-section and a spoiler aft-section. The spoiler fore-section includes a forward end configured to couple to a wing structure of an aircraft and a hinge end. The hinge end includes a first hinge coupling and a first retainer portion. The spoiler aft-section includes a second retainer portion and a second hinge coupling coupled to the first hinge coupling of the spoiler fore-section. The first retainer portion and the second retainer portion are configured to engage one another when the spoiler aft-section is aligned with the spoiler fore-section, and the first retainer portion and the second retainer portion are configured to disengage from one another responsive to the spoiler aft-section pivoting upward relative to the spoiler fore-section.
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公开(公告)号：US10647408B2
公开(公告)日：2020-05-12
申请号：US16210274
申请日：2018-12-05
Applicant: Wisk Aero LLC
Inventor： Chris Van Pelt , James Joseph Tighe
IPC: B32B5/26 , B64C9/02 , B32B5/04 , B32B7/02 , B29C70/30 , B64C9/32 , B64C3/20 , B64C9/00 , B29L31/22
Abstract: A composite structure with an integrated hinge is disclosed. In various embodiments, the composite structure includes a plurality of layers of fiber reinforced polymer material; and a hinge structure comprising one or more layers of bendably flexible hinge material a first region of which is interleaved between adjacent layers of said layers of fiber reinforced polymer material comprising the composite structure and bonded to said adjacent layers by bonding material comprising said composite structure, and a second region of which extends beyond said layers of fiber reinforced polymer material comprising the composite structure.
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公开(公告)号：US20200055585A1
公开(公告)日：2020-02-20
申请号：US16452787
申请日：2019-06-26
Applicant: Lucas Kai-Luen Hung
Inventor： Lucas Kai-Luen Hung
Abstract: An airfoil assembly comprising an airplane wing, a spoiler, and a flap for unmanned and high endurance aircraft. The spoiler is located on an upper surface of the airplane wing while the flap is located on a lower surface of the airplane wing. The spoiler and the flap can occupy at least one-third, and up to three-quarters, the chord span of the airplane wing. The spoiler and the flap are both capable of moving upwards and downwards with respect to the airplane wing through their respective frames.
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