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公开(公告)号：US20240375770A1
公开(公告)日：2024-11-14
申请号：US18644280
申请日：2024-04-24
Applicant: Textron Aviation Inc.
Inventor： Kelly Ray Laflin , Gonzalo Eduardo Mendoza , Corey Wailes Hagemeister
IPC: B64C23/06
Abstract: Wingtip devices configured to extend from the outboard ends of aircraft wings are designed to effectively reduce induced drag, but they necessarily produce form and skin-friction drag, and they may produce interference and compressibility drag. The present disclosure describes a scythe-shaped wingtip device (or ‘winglet’ or ‘extending member’) suitable for reducing the induced drag of an aircraft wing while minimizing other types of drag. A cutout in the wingtip device reduces the wetted area of the wingtip to minimize non-induced drag while the wingtip device still reduces induced drag like a conventional wingtip device. The cutout is configured in a trailing edge of the wingtip device.
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公开(公告)号：USD1049992S1
公开(公告)日：2024-11-05
申请号：US29806173
申请日：2021-09-01
Applicant: Textron Aviation Inc.
Designer： Shelby Nicole Page
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公开(公告)号：US12133605B1
公开(公告)日：2024-11-05
申请号：US18312131
申请日：2023-05-04
Applicant: Textron Aviation Inc.
Inventor： Bryan John Luedeke
Abstract: A metal curtain glide includes a spherical metal core coupled to a cable and having a polymer cup formed to fit a base of the metal core. The polymer cup includes a central opening for the cable to extend therethrough. An eyelet having a circular member with a connecting member is coupled to an end of the cable. A first member of a fastener assembly is coupled to the eyelet and configured to be removably secured to a second member of the fastener assembly that is coupled to a curtain. The curtain glide remains functional if the polymer cup fails.
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公开(公告)号：US12129037B2
公开(公告)日：2024-10-29
申请号：US18054624
申请日：2022-11-11
Applicant: Textron Aviation Inc.
Inventor： Robert Glynn Wiegers , Clinton Lee Thompson , Robin L. Young
CPC classification number: B64D13/08 , B60H1/0073 , G05D23/1931 , B64D2013/0618
Abstract: A method for heating an unpressurized aircraft includes receiving a desired air temperature, calculating a target duct air temperature based on the desired air temperature, determining an actual duct air temperature via a duct air temperature sensor, calculating a target modulation of one or more ram air valves based on a difference between the target duct air temperature and the actual duct air temperature, modulating one or more of the ram air valves based on the target modulation, introducing a bleed air from a turbine engine to a heat exchanger, introducing a temperature control air from one of the one or more ram air valves to the heat exchanger for cooling the bleed air to provide a temperature-controlled air, mixing the temperature-controlled air from the heat exchanger with an ejector ram air in an ejector, and providing air from the ejector to an occupied compartment of the unpressurized aircraft.
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公开(公告)号：US20240356151A1
公开(公告)日：2024-10-24
申请号：US18638428
申请日：2024-04-17
Applicant: Textron Aviation Inc.
IPC: H01M50/358 , H01M10/0525 , H01M50/112 , H01M50/249 , H01M50/375
CPC classification number: H01M50/358 , H01M10/0525 , H01M50/112 , H01M50/249 , H01M50/375 , H01M2220/20
Abstract: A battery module system includes one or more monoblocks each having one or more cells and a ventilation chamber configured to contain gases vented by the one or more cells. The system includes a channel having an exhaust vent that is in flow communication with each of the one or more monoblocks. A seal is positioned between each ventilation chamber of the one or more monoblocks and the channel and is actuatable when a threshold is achieved in the ventilation chamber associated with the seal.
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Patent Agency Ranking
公开(公告)号：USD1043189S1
公开(公告)日：2024-09-24
申请号：US29812252
申请日：2021-10-20
Applicant: Textron Aviation Inc.
Designer： Jason Michael Decker , Matthew William Reese , Barry John Ward , Matthew Allen Paul , Wallis Augusta Mead
Abstract: FIG. 1 is a perspective view of a fold over seat matting set showing our new design in an closed configuration;
FIG. 2 is a front view of the fold over seat matting set of FIG. 1 in an open configuration;
FIG. 3 is a left view of the fold over seat matting set of FIG. 1 in an open configuration;
FIG. 4 is a right view of the fold over seat matting set of FIG. 1 in an open configuration;
FIG. 5 is a top view of the fold over seat matting set of FIG. 1 in an open configuration;
FIG. 6 is a perspective view of the fold over seat matting set of FIG. 1 in a closed configuration;
FIG. 7 is a front view of the fold over seat matting set of FIG. 1 in a closed configuration;
FIG. 8 is a left view of the fold over seat matting set of FIG. 1 in a closed configuration;
FIG. 9 is a right view of the fold over seat matting set of FIG. 1 in a closed configuration; and,
FIG. 10 is a top view of the fold over seat matting set of FIG. 1 in a closed configuration.
In FIGS. 1-10, broken lines indicate environmental structure that forms no part of the claimed design.-
公开(公告)号：US20240295251A1
公开(公告)日：2024-09-05
申请号：US18590458
申请日：2024-02-28
Applicant: Textron Aviation Inc.
Inventor： Justin Birkey , Raymond Charters Maple
CPC classification number: F16F9/49 , B64C25/58 , F16F2222/126 , F16F2230/16
Abstract: A gas backflow restrictor system as part of an aircraft strut includes the strut defining an inner volume having a first chamber and a second chamber; an orifice plate positioned within the inner volume and separating the first chamber and the second chamber; a standpipe attached to the orifice plate and extending longitudinally within the inner volume, the standpipe having openings extending through a thickness of a wall forming the standpipe, the standpipe further defining an inner channel; and a restrictor mounted within the inner channel, the restrictor having a shelf extending into the inner channel and forming a central opening; the shelf is to reduce gaseous flow through one or more of the openings of the standpipe and toward the orifice plate.
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公开(公告)号：US20240286356A1
公开(公告)日：2024-08-29
申请号：US18583431
申请日：2024-02-21
Applicant: Textron Aviation Inc.
Inventor： Ron Tozier , Kyra Rubinstein , Ryan Binter
IPC: B29C64/35 , B29C64/118 , B29C64/209 , B29C64/232 , B29C64/241 , B33Y30/00 , B33Y40/00
CPC classification number: B29C64/35 , B29C64/118 , B29C64/209 , B29C64/232 , B29C64/241 , B33Y30/00 , B33Y40/00
Abstract: 3D printers perform additive manufacturing by depositing heated material (commonly plastic) onto a surface from a printer nozzle. During a 3D print, nozzles may “ooze” excess material, leading to deformities in 3D prints. Disclosed is an anti-ooze mechanism that covers up 3D printer nozzles when they are not being used. A servo moves a nozzle shield in front of and away from a nozzle while a 3D print is happening so that no ooze drips onto a 3D print or otherwise escapes from a printer nozzle onto the printer bed. Moreover, the servo can move the nozzle shield quickly to minimize the amount of time that a nozzle spends uncovered, and the nozzle shield is also capable of “scraping off” excess material from the nozzle head.
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公开(公告)号：US20240280059A1
公开(公告)日：2024-08-22
申请号：US18581952
申请日：2024-02-20
Applicant: Textron Aviation Inc.
Inventor： Trey Marcus Siemens , Burl Justin Fletcher
CPC classification number: F02C9/18 , B64D13/06 , B64D2013/0618 , F05D2220/323 , F05D2260/606 , F05D2270/306 , F05D2270/335
Abstract: A pneumatic flow control system for an aircraft includes a control system operating and implementing a software program through a digital environment, the software program having one or more rules; a sensor in digital communication with the control system, the sensor to relay engine power data to the control system; an electronically controlled valve in digital communication with the control system, the electronically controlled valve to control an amount of bleed air flowing therethrough; a first rule defining an engine power parameter and a valve position for the electronically controlled valve and using the engine power data relayed from the sensor, receiving data equating to the engine power parameter activates transmitting a command to the electronically controlled valve to adjust to the valve position; and the valve position is set to restrict flow through the valve to below a threshold limit.
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公开(公告)号：US20240240695A1
公开(公告)日：2024-07-18
申请号：US18410832
申请日：2024-01-11
Applicant: Textron Aviation Inc.
Inventor： Blake David Raybern
IPC: F16G11/12
CPC classification number: F16G11/12
Abstract: A cable tensioner for adjusting the tension in various cables. It may be used with a variety of cables including those that have flexible members routed through bendable sheaths. The cable tensioner includes a worm gear arrangement located within a housing, where the worm gear takes the form of a worm screw engaged with a spur gear. The spur gear may then be engaged with teeth on a movable sleeve. The end of a cable is secured within the sleeve and the tension in the cable can be adjusted by moving the sleeve via the worm gear.
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