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公开(公告)号：US20240017823A1
公开(公告)日：2024-01-18
申请号：US17867231
申请日：2022-07-18
Applicant: Textron Innovations Inc.
Abstract: In an embodiment, an aircraft includes a drive system, a main engine coupled to the drive system to provide first power, and a supplemental engine coupled to the drive system to provide second power additive to the first power. The aircraft also includes a control system to control the main engine and the supplemental engine to optimize usage of the supplemental engine. The control system is operable to maintain the supplemental engine in a reduced power state at least until a determination is made that supplemental power is needed to satisfy a total power demand of the drive system. The control system is also operable to determine that supplemental power is needed to satisfy the total power demand of the drive system. The control system is further operable to increase a power level of the supplemental engine in response to the determination that supplemental power is needed.
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公开(公告)号：US20230327292A1
公开(公告)日：2023-10-12
申请号：US18206610
申请日：2023-06-06
Applicant: Textron Innovations Inc.
Inventor： Michael Raymond Hull , Steven Loveland , Yue Fan
IPC: H01M50/512 , B64D27/24 , B60L50/64 , B64C29/00 , B60L58/10 , H01M10/42 , H01M50/249 , H01M50/209
CPC classification number: H01M50/512 , B64D27/24 , B60L50/64 , B64C29/00 , B60L58/10 , H01M10/425 , H01M50/249 , H01M10/4207 , H01M50/209 , H01M2010/4271 , B64D2221/00 , B60L2200/10 , H01M2220/20
Abstract: A modular battery system includes an array of battery modules arranged in at least one stack. Each battery module includes a plurality of battery cells, a first side having positive and negative receptacles and a second side, that is opposite of the first side, having positive and negative plugs. The receptacles and plugs are configured such that adjacent battery modules in a side-by-side relationship are electrically coupled together via plug and receptacle connections and such that the battery modules are electrically coupled together in parallel. An interconnection electrically couples each stack of battery modules together via plug and receptacle connections with one of the battery modules in each stack such that the stacks of battery modules are electrically coupled together in parallel. Each of the battery modules includes a thermal conditioning system configured to thermally isolate the battery module from the other battery modules.
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公开(公告)号：US20250100680A1
公开(公告)日：2025-03-27
申请号：US18472933
申请日：2023-09-22
Applicant: Textron Innovations Inc.
Inventor： Lancer Drake Halcom , Kyle Thomas Cravener
Abstract: An aircraft that has a blade position control system (BPCS). The BPCS includes an actuator, a multilobe component configured for at least one of longitudinal movement along a mast axis as a function of actuation of the actuator and rotational movement relative to the mast axis as a function of actuation of the actuator. Movement of the multilobe component selectively restricts at least one of pitch movement and folding of a plurality of rotor blades.
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公开(公告)号：US12261511B2
公开(公告)日：2025-03-25
申请号：US17748238
申请日：2022-05-19
Applicant: Textron Innovations Inc.
Inventor： Michael Glynn Glucksman
Abstract: A technique for generating electrical power from an engine in an aerial vehicle includes providing an alternator disk structure (ADS) between the engine and a propeller of the vehicle. The ADS is disposed concentrically with an engine drive shaft that drives the propeller and includes at least two concentric regions, a first region having a stator and a second region having a rotor. The first region is rotationally fixed relative to the engine, and the second region is coupled to a drive shaft of the engine. As the engine rotates the drive shaft, the rotor disposed in the second region spins concentrically relative to the stator disposed in the first region, thereby inducing electrical current in windings of the stator. The rotor and the stator thus work together to generate electrical power, which may be conveyed from the stator to electrical subsystems and controls of the vehicle.
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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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Patent Agency Ranking
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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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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