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.

公开(公告)号：US20230159152A1

公开(公告)日：2023-05-25

申请号：US18057037

申请日：2022-11-18

Applicant: Textron Aviation Inc.

Inventor： Justin Eugene Thompson ,  Kenneth Matthew Cumming ,  Morgan Christopher Brown ,  Anthony Westhoff ,  Andrew Kent Johnson

IPC: B64C1/14 ,  E05F15/603 ,  E05F15/70

CPC classification number: B64C1/1469 ,  E05F15/603 ,  E05F15/70

Abstract: A system for an automated cabin-divider door for an aircraft includes a door, a motor for moving the door to an open position, a limit switch configured to detect when the door is in a fully open position and to stop the motor, and electronics coupling the motor and the limit switch to an avionics system. The avionics system determines when the door is to be opened and provides a signal to the motor for moving the door to the fully open position. A method for automatically opening the cabin-divider door includes determining whether the aircraft is on the ground or in flight, determining whether the aircraft is taxiing, and determining whether the aircraft is in a final phase of approach. When the aircraft is taxiing or in the final phase of approach, the method includes sending a command signal to the motor for opening the cabin-divider door.

公开(公告)号：US20230115357A1

公开(公告)日：2023-04-13

申请号：US18045553

申请日：2022-10-11

Applicant: Textron Aviation Inc.

Inventor： Barry John Ward ,  Matthew William Reese ,  Jason Michael Decker ,  Matthew Allen Paul

IPC: B64D11/06

Abstract: A foldable vehicle seat includes a seat base having a seat support frame, a seat back extending from the seat base, and a foldable section connected to the seat back. The folded section has a folded and unfolded configuration, and comprises a hinge mechanism with a pivot point, a first support, a second support, and a top surface configured to store luggage thereon. The first support is connected to the hinge mechanism and is rotatable about the pivot point. Likewise, the second support is connected to the hinge mechanism and is rotatable about the pivot point. The first and second supports contain first and second magnets, respectively, which are configured to retain the foldable section in the folded configuration.

公开(公告)号：US11528165B2

公开(公告)日：2022-12-13

申请号：US16225056

申请日：2018-12-19

Applicant: Textron Aviation Inc.

Inventor： Joseph Andrew Ohol ,  Robin L. Young

IPC: H04L12/403 ,  B64F5/60 ,  H04L67/12 ,  H04L12/46 ,  H04L12/40

Abstract: A remote sensor data acquisition system for an aircraft includes a plurality of remote sensors co-located onboard the aircraft and adapted to measure one or more aircraft-related parameters. A remote sensor interface is co-located with the plurality of remote sensors. The remote sensor interface includes a communication bus having a plurality of nodes to transmit data from the plurality of remote sensors. A plurality of subsystems are each adapted to receive data from the plurality of remote sensors simultaneously and in real time via the remote sensor interface. A remote sensor data acquisition method for an aircraft includes sensing one or more parameters onboard the aircraft via a plurality of remote sensors and transmitting sensor data from the plurality of remote sensors to a plurality of subsystems independently and in real time via a remote sensor interface.