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.

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

IPC: F02C9/18 ,  B64D13/06

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.

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.

公开(公告)号：US20240227078A1

公开(公告)日：2024-07-11

申请号：US18405035

申请日：2024-01-05

Applicant: Textron Aviation Inc.

Inventor： Royce Heick ,  Aaron Paul Shirley ,  Cameron Enderson

IPC: B23K26/211 ,  B23K26/38 ,  B23K101/24 ,  B23K103/00

CPC classification number: B23K26/211 ,  B23K26/38 ,  B23K2101/24 ,  B23K2103/42

Abstract: A method of locating a stake to a floor assembly jig includes providing a floor assembly jig and a stake having a plurality of segments, laser cutting one or more slots into a structural member of the floor assembly jig, inserting at least one segment of the stake into the one or more slots thereby providing a substantially precise position and alignment of the stake with respect to the floor assembly jig, and securing the stake to the floor assembly jig to maintain the substantially precise position and alignment of the stake.

公开(公告)号：USD1031290S1

公开(公告)日：2024-06-18

申请号：US29872479

申请日：2023-03-14

Applicant: Textron Aviation Inc.

Designer： Merril Binford Williams ,  Frank Joseph Rowe

Abstract: FIG. 1 is a perspective view showing our new design of a cockpit crew seating;
FIG. 2 is another perspective view of the cockpit crew seating of FIG. 1;
FIG. 3 is a rear perspective view of the cockpit crew seating of FIG. 1;
FIG. 4 is a front view of the cockpit crew seating of FIG. 1;
FIG. 5 is a rear view of the cockpit crew seating of FIG. 1;
FIG. 6 is a side view of the cockpit crew seating of FIG. 1;
FIG. 7 is a side view opposite that of FIG. 6 showing the cockpit crew seating of FIG. 1;
FIG. 8 is a top view of the cockpit crew seating of FIG. 1; and,
FIG. 9 is a bottom view of the cockpit crew seating of FIG. 1.
In FIG. 9, broken lines indicate environmental structure that forms no part of the claimed design.

公开(公告)号：US11999271B2

公开(公告)日：2024-06-04

申请号：US17578546

申请日：2022-01-19

Applicant: Textron Aviation Inc.

Inventor： Barry John Ward

IPC: B60N2/08 ,  B60N2/36

CPC classification number: B60N2/0862 ,  B60N2/366

Abstract: A latching mechanism configured to secure a first component and a second component. The latching mechanism includes a locking plate that operatively engages a first latch plate and a second latch plate. The plates each include an end that inserts into a slot located on the second component, therein securing the first component to the second component. Actuation of the latching mechanism displaces the plates, therein releasing the ends from the slot and allowing for movement of the first component in relation to the second component.

公开(公告)号：USD1022845S1

公开(公告)日：2024-04-16

申请号：US29811182

申请日：2021-10-12

Applicant: Textron Aviation Inc.

Designer： Frank Joseph Rowe ,  Matthew R. Harrell ,  David Wayne Davis ,  Sergio R. Martinez ,  Brent Todd Coppock

Abstract: FIG. 1 is a perspective view of a side ledge for aircraft showing our new design;
FIG. 2 is a front view of the side ledge for aircraft of FIG. 1;
FIG. 3 is a left view of the side ledge for aircraft of FIG. 1;
FIG. 4 is a right view of the side ledge for aircraft of FIG. 1; and,
FIG. 5 is a top view of the side ledge for aircraft of FIG. 1.
In FIGS. 1-5, the broken lines shown in the drawings depict portions of the side ledge for aircraft that form no part of the claimed design.

公开(公告)号：US11912415B2

公开(公告)日：2024-02-27

申请号：US17587832

申请日：2022-01-28

Applicant: Textron Aviation Inc.

Inventor： Todd Alan Thisius ,  Tim Todd Razey

IPC: B64D11/06 ,  B60N2/07 ,  B60N2/015 ,  B60N2/005

CPC classification number: B64D11/0696 ,  B60N2/005 ,  B60N2/01516 ,  B60N2/0715 ,  B60N2/0722

Abstract: A vibration-reducing insert is usable to reduce vibration or play between two metal aircraft components. The insert rotates on a fastener, and includes a shelf that projects into the gap and operates as an indexable cam to establish an appropriate compression in an engaged portion of the shelf.

公开(公告)号：US20230257110A1

公开(公告)日：2023-08-17

申请号：US18170247

申请日：2023-02-16

Applicant: Textron Aviation Inc.

Inventor： Justin Birkey

IPC: B64C25/60 ,  F16F9/06

CPC classification number: B64C25/60 ,  F16F9/062

Abstract: A compression-force spike reduction system for a strut includes a first chamber and a second chamber, an orifice plate disposed within the strut between the first chamber and the second chamber, a hydraulic fluid disposed within the first chamber and the second chamber, and a compressible portion disposed in the second chamber. The orifice plate includes at least one orifice configured for the hydraulic fluid to flow through. During compression or extension of the strut, hydraulic fluid is exchanged between the first chamber and the second chamber. The compressible portion contains a compressible medium configured to buffer spikes in compression force of the strut. A compression-force spike reduction method includes filling the second chamber partially with the incompressible hydraulic fluid, and filling a remaining portion of the second chamber with a compressible medium.

公开(公告)号：US20230227148A1

公开(公告)日：2023-07-20

申请号：US18155036

申请日：2023-01-16

Applicant: Textron Aviation Inc.

Inventor： Matthew James Anker

IPC: B64C13/50

CPC classification number: B64C13/50

Abstract: A servo drive vernier control for aircraft having a push-pull mechanism configured for manual actuation by a user includes a push rod mechanically coupled with an input knob. The push rod is configured for manual actuation via the input knob. An electromechanical control system is operatively coupled with the push rod for providing automated operation of the push rod. The electromechanical system includes a motor operatively coupled to the push rod. The motor is configured to rotate the push rod for actuating the push-pull mechanism. A controller is communicatively coupled to the motor for enabling electronic control of the push-pull mechanism.