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公开(公告)号：US12208923B2
公开(公告)日：2025-01-28
申请号：US18172955
申请日：2023-02-22
Applicant: Rohr, Inc.
Inventor： Jennifer Davis
IPC: B64F5/10 , B29C45/00 , B29C45/14 , B29C45/26 , B64C9/00 , B29C31/00 , B29C33/76 , B29C70/54 , B29L31/00 , B29L31/30 , B64C3/20
Abstract: A tool for fabricating a control surface is disclosed. In various embodiments, the tool includes a first block defining a longitudinal direction running between a leading edge end and a trailing edge end; a first sidewall spaced a first lateral distance from the first block to form a first closeout channel running in the longitudinal direction between the first block and the first sidewall; and a second sidewall configured to form a second closeout channel running in the longitudinal direction, the second closeout channel disposed laterally opposite the tool from the first closeout channel.
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公开(公告)号：US12103678B2
公开(公告)日：2024-10-01
申请号：US18139187
申请日：2023-04-25
Applicant: AeroVironment, Inc.
Inventor： Carlos Thomas Miralles , Robert Nickerson Plumb , Tony Shuo Tao , Nathan Olson
IPC: B64C3/56 , B64C3/44 , B64C3/50 , B64C5/12 , B64C9/02 , B64C9/08 , B64C9/18 , B64C9/36 , B64C11/00 , B64C13/18 , B64C13/34 , B64C39/02 , B64U30/40 , B64U40/10 , B64C9/00 , B64U10/25 , B64U20/50 , B64U30/12 , B64U30/293 , B64U70/00 , B64U101/15
CPC classification number: B64C3/56 , B64C3/44 , B64C3/50 , B64C5/12 , B64C9/02 , B64C9/08 , B64C9/18 , B64C9/36 , B64C11/00 , B64C13/18 , B64C13/34 , B64C39/024 , B64U30/40 , B64U40/10 , B64C2009/005 , B64U10/25 , B64U20/50 , B64U30/12 , B64U30/293 , B64U70/00 , B64U2101/15 , B64U2201/00 , B64U2201/104 , B64U2201/20
Abstract: 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：US12097953B2
公开(公告)日：2024-09-24
申请号：US17703701
申请日：2022-03-24
Applicant: Airbus Operations Ltd.
Inventor： William Tulloch
Abstract: An aircraft wing including a wingbox with an upper cover, a lower cover, a forward spar and a rear spar. A leading edge of a trailing edge panel is attached to the wingbox. A support structure is attached to the wingbox. A kinked link includes a first arm, a second arm, and a corner where the first and second arms meet. The first arm of the kinked link is pivotally attached to the trailing edge panel at a first pivot joint, and the second arm of the kinked link is pivotally attached to the support structure at a second pivot joint.
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公开(公告)号：US20240274018A1
公开(公告)日：2024-08-15
申请号：US18646203
申请日：2024-04-25
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Michael Mast , Yuta Morioka , Jeffrey Glenn
Abstract: Flight guidance methods, systems, and aircraft systems providing assist-to-land and emergency land (EL) functions. The method includes generating a visual indication of the availability and status of an assist-to-land function and an EL function when the current altitude of the aircraft exceeds an altitude threshold. When in assist-to-land, visual and audible flight guidance can be generated to guide the pilot to a safe landing at a selected runway or at a best runway for the conditions. Functions can be activated by user manipulations of interface objects and/or by software determinations. Software determinations to enter the EL function can automatically control the flying of the aircraft along an approach profile to a safe landing at a nearest suitable airport. EL determinations can be made based on pilot incapacitation.
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公开(公告)号：US12049061B2
公开(公告)日：2024-07-30
申请号：US16845133
申请日：2020-04-10
Applicant: The Boeing Company
Inventor： Stanley W. Stawski
IPC: B29D99/00 , B29C35/02 , B29C39/14 , B29C63/00 , B32B1/08 , B32B3/06 , B32B5/02 , B32B5/26 , B32B7/04 , B32B15/092 , B32B15/14 , B64C3/20 , B64C9/00 , B64F5/10 , B29C70/02
CPC classification number: B32B15/092 , B29C35/02 , B29C39/14 , B29C63/00 , B29D99/0025 , B32B1/08 , B32B3/06 , B32B5/02 , B32B5/26 , B32B7/04 , B32B15/14 , B64C3/20 , B64C9/00 , B64F5/10 , B29C35/0227 , B29C70/028 , B29D99/0028 , B32B2260/023 , B32B2260/046 , B32B2262/106 , B32B2307/50 , B32B2307/538 , B32B2603/00 , B32B2605/08 , B32B2605/18 , Y02T50/40
Abstract: A method for forming a composite article includes adding an upper skin at least partially over a failsafe torque tube. The failsafe torque tube includes an inner tube and an outer tube. The method also includes adding a lower skin at least partially under the failsafe torque tube. The upper skin, the lower skin, and the outer tube are made of a composite material. The method also includes co-curing the upper skin, the lower skin, and the outer tube together to produce the composite article.
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公开(公告)号：US12043376B2
公开(公告)日：2024-07-23
申请号：US16647817
申请日：2018-09-06
Applicant: AMSL Innovations Pty Ltd
Inventor： Andrew Dudley Moore
IPC: B64C29/00 , B60L15/20 , B64C3/38 , B64C9/00 , B64C9/16 , B64C13/00 , B64C27/52 , B64C27/80 , B64C27/82 , B64C39/06 , B64D27/24
CPC classification number: B64C29/0033 , B60L15/20 , B64C3/38 , B64C9/00 , B64C9/16 , B64C13/00 , B64C27/52 , B64C27/80 , B64C27/82 , B64C39/068 , B64D27/24 , B60L2200/10 , B64C2027/8227
Abstract: A vertical take-off and landing (VTOL) aircraft (10) comprises a fuselage (24) first and second forward wings (20, 22) and first and second rearward wings (30, 32), each wing having a fixed leading edge (25, 35) and a trailing control surface (50) which is pivotal about a generally horizontal axis. Electric rotors (60) are mounted to the wings (20, 22, 30, 32), the electric rotors (60) being pivotal with the trailing control surface (50) between a first position in which each rotor (60) has a generally vertical axis of rotation, and a second position in which each rotor (60) has a generally horizontal axis of rotation; wherein at least one of the wings (20, 22, 30, 32) has a first and a second electric rotor (60) which are each mounted having non-parallel axes of rotation so that the thrust lines of the first and second electric rotors are different.
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公开(公告)号：US12006030B2
公开(公告)日：2024-06-11
申请号：US16857954
申请日：2020-04-24
Inventor： Steven C. Geuther , David D. North , Robert G. McSwain , Michael D. Patterson , Gregory Howland , Jared S. Fell , Christopher M. Cagle , Xiaofan Fei , Siena K. S. Whiteside , David A. Hare
CPC classification number: B64C29/0025 , B64C9/00 , B64C9/04 , B64C11/46 , B64C13/02 , B64C39/08 , B64D27/24 , B64D31/02 , B64C2009/005
Abstract: An aircraft wing configuration for a vertical or a short take-off and landing aircraft having a plurality of propeller-blown wings mounted at different longitudinal locations along a fuselage of the vertical take-off and landing aircraft, producing two or more lifting surfaces, fixed at a predetermined acute wing angle greater than 0° and substantially less than 90° relative to a horizontal plane, and having a plurality of flaps disposed behind the wings. The configuration has a plurality of propellers distributed in front of the plurality of wings producing two or more lifting surfaces and mounted such that the wings are externally blown by forced airstreams from the propellers. The propellers produce distributed thrust components, and the plurality of flaps are in the forced airstreams of the propellers when one or more of the flaps is in an extended position.
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公开(公告)号：US11970275B2
公开(公告)日：2024-04-30
申请号：US17583467
申请日：2022-01-25
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Danny Abramov , Shay Hemo
CPC classification number: B64D27/24 , B64C11/46 , B64C29/0025 , B64U50/13 , B64C2009/005 , B64C9/38
Abstract: An air vehicle is provided including: a main lift generating wing arrangement having a port wing and a starboard wing, empennage and main propulsion system. The air vehicle further includes a distributed electrical propulsion (DEP) system having secondary electrical propulsion units coupled to each one of the port wing and the starboard wing. The main propulsion system is configured for providing sufficient thrust such as to enable powered aerodynamic flight of the air vehicle including at least: powered aerodynamic take off absent operation of the DEP system; and powered aerodynamic landing absent operation of the DEP system. The DEP system is configured for selectively providing at least augmented lift to the main lift generating wing arrangement in at least landing. A method for landing an air vehicle on a moving platform under separated wake conditions is also provided.
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公开(公告)号：US11841713B2
公开(公告)日：2023-12-12
申请号：US16736036
申请日：2020-01-07
Applicant: Gulfstream Aerospace Corporation
Inventor： Jong-Yeob Shin , Gi-Yun Chung , Lakmal Kaviratna
CPC classification number: G05D1/0833 , B64C9/00 , B64C13/0421 , B64C13/16 , B64C13/26 , B64D43/02 , G05D1/0808 , G05D1/0816
Abstract: Flight control systems, flight control laws, and aircraft are provided. An flight control system includes an input configured to receive a pitch rate command, a processor operative to receive the pitch angle command, to calculate a pitch angle saturation limit, to compare the sum of the pitch rate command, the scaled pitch rate, and the scaled pitch angle to the pitch angle saturation limit, to convert the pitch rate command system to the pitch angle command system in response to the sum exceeding the pitch angle saturation limit value to limit the pilot pitch-up pitch rate command, and to couple the pitch rate command to an aircraft control surface for the failure case of one of control surface, and the aircraft control surface configured to adjust an aircraft control surface setting in response to the pitch rate command and/or pitch angle command to protect an aircraft from being in stall condition.
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公开(公告)号：US11787539B2
公开(公告)日：2023-10-17
申请号：US17220137
申请日：2021-04-01
Applicant: Xingkang Li , Heng Ren , Qiang Li , Xingjian Li
Inventor： Xingkang Li , Heng Ren , Qiang Li , Xingjian Li
CPC classification number: B64C37/00 , B64C1/065 , B64C5/00 , B64C9/00 , B64C27/68 , B64D27/10 , B64D31/00 , B64C2009/005
Abstract: A convertible aircraft system is provided that can convert to a helicopter configuration, an airplane configuration, or a gyroplane configuration before, during, or after flight. The convertible aircraft system includes a fuselage, a proximal flight assembly, a distal flight assembly, a support spar, and a tail assembly. The fuselage is the main structural body of the present invention. The proximal flight assembly and the distal flight assembly are the flight system of the present invention. The support spar provides an axis of rotation and a pole support for the proximal flight assembly and the distal flight assembly. The tail assembly provides stability during flight of the present invention. In more detail, the tail assembly may comprise at least one vertical stabilizer, at least one horizontal stabilizer, and at least one rudder in order to provide stability during flight of the present invention.
