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公开(公告)号：US12234024B2
公开(公告)日：2025-02-25
申请号：US18226526
申请日：2023-07-26
Applicant: Textron Innovations Inc.
Abstract: An aircraft nacelle includes a forward cruise inlet, a forward-cruise-inlet conduit coupled to the forward cruise inlet and operable to supply air from the forward cruise inlet to an engine housed by the aircraft nacelle, an inlet barrier filter, an inlet-barrier-filter compartment coupled to the inlet barrier filter, a plurality of gills coupled between the inlet-barrier-filter compartment and the engine and operable to be in an open state and a closed state, a filter-purge door coupled to the inlet-barrier-filter compartment and operable to be in a closed state and an open state. When the plurality of gills are in the closed state and the filter-purge door is in the open state, air from the filter-purge door flows from the inlet-barrier-filter compartment through the inlet barrier filter.
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公开(公告)号：US20250058643A1
公开(公告)日：2025-02-20
申请号：US18233555
申请日：2023-08-14
Applicant: Textron Innovations Inc.
Abstract: Techniques to control a utility vehicle involve initially setting a maximum speed constraint imposed on the utility vehicle to an initial value. Such techniques further involve receiving a state of charge signal that indicates a current state of charge of a lithium battery which provides electric power for utility vehicle propulsion. Such techniques further involve, based on the state of charge signal that indicates the current state of charge of the lithium battery, adjusting the maximum speed constraint imposed on the utility vehicle from the initial value to an adjusted value that is different from the initial value.
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公开(公告)号：US12221207B2
公开(公告)日：2025-02-11
申请号：US18347737
申请日：2023-07-06
Applicant: Textron Innovations Inc.
Inventor： Amarjit Kizhakkepat , Mark Adam Wiinikka
Abstract: A back-to-back spherical bearing assembly for a rotary system of a rotary aircraft includes a spherical bearing member having an interior cavity and a spherical bearing surface defining a bearing focal point, a first elastomeric and a second elastomeric bonded to the spherical bearing surface on opposite sides of the bearing focal point, an inboard attachment bonded to the first elastomeric and configured to be secured to a rotor hub of the rotary system, and an outboard attachment bonded to the second elastomeric and configured to be secured to a rotor blade of the rotary system.
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公开(公告)号：US12214870B2
公开(公告)日：2025-02-04
申请号：US17941776
申请日：2022-09-09
Applicant: Textron Innovations Inc.
Inventor： Bharath Ramamurthy
Abstract: In certain embodiments, a rotorcraft includes a first engine, a second engine, a primary engine-start system for the first engine, a fast-start engine-start system for the first engine, and a computer system. The computer system is configured to detect a failure of the second engine during a reduced engine operation (REO) flight mode in which the first engine has been intentionally shut down inflight and the second engine is to remain operational, and to automatically initiate, in response to detecting the failure of the second engine during the REO flight mode, an automatic restart of the first engine using the fast-start engine-start system.
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公开(公告)号：US12214860B2
公开(公告)日：2025-02-04
申请号：US18059002
申请日：2022-11-28
Applicant: Textron Innovations Inc.
Inventor： Kyle Thomas Cravener , Andrew Ryan Maresh , Brady Garrett Atkins , Kynn J. Schulte , Troy Schank
Abstract: Embodiments are directed to a blade lock comprising a fold lock adapted to prevent folding of a rotor blade in a fold-lock position and to allow folding of the rotor blade in a pitch-lock position. The blade lock further comprises a pitch lock adapted to allow pitch movement of a rotor blade in a fold-lock position and to prevent pitch movement of the rotor blade in the pitch-lock position. A spring-loaded link pivotally connects both the fold lock and the pitch lock and is adapted to provide passive, overcenter locking in the fold-lock position. An actuator is coupled to the pitch lock and is adapted to move the pitch lock and the fold lock between the fold-lock and pitch-lock positions.
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Patent Agency Ranking
公开(公告)号：US20250033786A1
公开(公告)日：2025-01-30
申请号：US18226526
申请日：2023-07-26
Applicant: Textron Innovations Inc.
Abstract: An aircraft nacelle includes a forward cruise inlet, a forward-cruise-inlet conduit coupled to the forward cruise inlet and operable to supply air from the forward cruise inlet to an engine housed by the aircraft nacelle, an inlet barrier filter, an inlet-barrier-filter compartment coupled to the inlet barrier filter, a plurality of gills coupled between the inlet-barrier-filter compartment and the engine and operable to be in an open state and a closed state, a filter-purge door coupled to the inlet-barrier-filter compartment and operable to be in a closed state and an open state. When the plurality of gills are in the closed state and the filter-purge door is in the open state, air from the filter-purge door flows from the inlet-barrier-filter compartment through the inlet barrier filter.
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公开(公告)号：US20250010982A1
公开(公告)日：2025-01-09
申请号：US18347737
申请日：2023-07-06
Applicant: Textron Innovations Inc.
Inventor： Amarjit KIZHAKKEPAT , Mark Adam WIINIKKA
Abstract: A back-to-back spherical bearing assembly for a rotary system of a rotary aircraft includes a spherical bearing member having an interior cavity and a spherical bearing surface defining a bearing focal point, a first elastomeric and a second elastomeric bonded to the spherical bearing surface on opposite sides of the bearing focal point, an inboard attachment bonded to the first elastomeric and configured to be secured to a rotor hub of the rotary system, and an outboard attachment bonded to the second elastomeric and configured to be secured to a rotor blade of the rotary system.
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公开(公告)号：US20240417072A1
公开(公告)日：2024-12-19
申请号：US18821928
申请日：2024-08-30
Applicant: Textron Innovations Inc.
Inventor： Levi Charles Hefner , Kevin Fisher , Manuel Adrian Gonzalez
Abstract: A tailsitter aircraft includes an airframe having first and second wings with first and second pylons extending therebetween, a thrust array attached to the airframe, payloads and payload saddle assemblies coupled to the pylons each configured to secure a respective payload. The thrust array includes propulsion assemblies configured to transition the airframe between a forward flight orientation for wing-borne lift and a VTOL orientation for thrust-borne lift. Each payload saddle assembly includes a latch assembly and a retainer configured to secure the respective payload against a respective pylon. A latch assembly is movable between various positions including an open position and a closed position and is configured to secure the respective payload in the closed position and release the respective payload in the open position. Each latch assembly is configured to move from the closed position to the open position to release the respective payload in the VTOL orientation.
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公开(公告)号：US20240409239A1
公开(公告)日：2024-12-12
申请号：US18333354
申请日：2023-06-12
Applicant: Textron Innovations Inc.
Inventor： Juan Li
Abstract: In certain embodiments, a method includes accessing, by a processing device, actual operating condition information for an operating condition parameter associated with actual operation of a vehicle. The actual operating condition information corresponds to sensor measurements associated with a vehicle component of the vehicle. The method includes analyzing, by the processing device and using an artificial intelligence model, the actual operating condition information to generate predicted load information for the vehicle component. The method includes determining, according to the predicted load information, an estimated fatigue life for the vehicle component that is individualized for the vehicle component.
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公开(公告)号：US20240401672A1
公开(公告)日：2024-12-05
申请号：US18329189
申请日：2023-06-05
Applicant: Textron Innovations Inc.
Inventor： Charles J. Ott , Nathaniel Bernklau , Trenton Hamm
Abstract: An improved compound planetary gear system. In embodiments, a compound planetary gear system includes at least one planet pinion including a main shaft having a first gear for meshing with a sun gear and a second gear for meshing with a ring gear, and a carrier for supporting the at least one planet pinion. Teeth of the first gear are configured with a first helical angle with respect to a longitudinal angle of the at least one planet pinion, teeth of the second gear are configured with a second helical angle with respect to the longitudinal angle of the at least one planet pinion, the first helical angle different from the second helical angle.
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