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.

公开(公告)号：US11312500B2

公开(公告)日：2022-04-26

申请号：US15708411

申请日：2017-09-19

Applicant: Textron Aviation Inc.

Inventor： Robert Glynn Wiegers ,  Cristopher Robert Schroeder

IPC: B64D15/16

Abstract: An electro-pneumatic de-icer for an airfoil includes an electrically-powered compressor for compressing air, an air-storage tank for storing compressed air, a source of negative pressure, an airfoil pneumatic boot, and a control valve located between 1) the air-storage tank, 2) the source of negative pressure, and 3) the pneumatic boot for cycling between compressed air to inflate the pneumatic boot and negative pressure to deflate the pneumatic boot for cracking accumulated ice on the airfoil. An airfoil de-icing method lacking engine bleed air extraction includes compressing air with an electrically-powered compressor, storing high-pressure air from the compressor in an air-storage tank, delivering high-pressure air from the air-storage tank to inflate a pneumatic boot located along an airfoil, providing a negative-pressure source, deflating the pneumatic boot with the negative-pressure source, and alternating between inflating and deflating the pneumatic boot for cracking accumulated ice on the airfoil.

公开(公告)号：US11148788B2

公开(公告)日：2021-10-19

申请号：US15430661

申请日：2017-02-13

Applicant: Textron Aviation Inc.

Inventor： David James Swanson

IPC: B64C23/06

Abstract: Embodiments of the present disclosure include a curved planar wingtip for a straight wing and a curved planar wingtip for a swept wing of an aircraft. The curved planar wingtips include a member that extends from the end of the wing in a direction aft of the wing trailing edge while remaining substantially planar with the wing. The curved planar wingtips curve continuously from leading and trailing edges of the wing to form a tip located aft of the wing. Other embodiments of the curved planar wingtip are configured for a horizontal or vertical tail. Yet another embodiment includes a curved wingtip that extends aft of a trailing edge of the wing by a distance greater than the curved wingtip extends above a top surface of the wing.

公开(公告)号：US20210155127A1

公开(公告)日：2021-05-27

申请号：US17101298

申请日：2020-11-23

Applicant: Textron Aviation Inc.

Inventor： Brent William Last

IPC: B60N2/30 ,  F16B2/18 ,  B60N2/005

Abstract: A seat configured for removably securing to a track includes a quick-release fitting for operation by hand to releasably secure a bottom end of a seat leg to a floor-mounted track for facile adjustment and removal of the seat. A threaded stud includes a shaft portion arranged through an opening in an end of the seat leg and a radially extending base. A pivot mechanism has a through-hole arranged around the shaft portion of the threaded stud. A first transverse member and a second transverse member each extend transversely from the pivot mechanism in opposite directions along a pivot axis. A lever is configured to pivot about the pivot axis causing the threaded stud to move up or down via the pivot mechanism, which raises and lowers the radially extending base for alternately securing the seat leg to the track and releasing the seat leg from the track.

公开(公告)号：US11014690B2

公开(公告)日：2021-05-25

申请号：US16048947

申请日：2018-07-30

Applicant: Textron Aviation Inc.

Inventor： David Wayne Davis ,  Todd Alan Thisius ,  Chris Trask ,  Chris Pinkerton ,  Alec Charles Willford

IPC: B64F5/00 ,  G09B25/02 ,  B64F5/10

Abstract: A system and method for simulating a structure is disclosed. An adjustable interior mockup for simulating a structure has a base with a first elongated side and a second elongated side, the first elongated side being nonadjacent the second elongated side; and an adjustable frame secured to the base. The adjustable frame includes a plurality of girder members secured along the first and second elongated sides to form an arc; a plurality of brackets; a plurality of arms having a latch attached to one end; and a sheet of fabric. The girders are securely fastened along the first elongated side of the base at predetermined intervals; the brackets are secured to the girders; the arms are received by the brackets and adjustably anchored to the girders via a fastener; and the latches engage the sheet of fabric, thus pulling the fabric into a shape that resembles the structure.

公开(公告)号：US11014684B2

公开(公告)日：2021-05-25

申请号：US15927228

申请日：2018-03-21

Applicant: Textron Aviation Inc.

Inventor： Vernon Weng-Yew Chang ,  Charles Bernard Beuning ,  Adam Blake Wolfe ,  Phuong Ngoc Ta ,  Mark Christopher Hansen

IPC: B64D41/00 ,  H02J1/00 ,  B64D13/06 ,  H02J7/00 ,  G05D1/00 ,  H02M7/44 ,  H02J7/14 ,  B64F5/40 ,  H02J1/10 ,  H01M50/20 ,  B64F5/60 ,  B64D45/00 ,  G01F9/00 ,  G07C5/00 ,  H01M10/42 ,  H01M50/50 ,  H01M50/543

Abstract: An expedited preflight readiness system for aircraft includes a power source having one or more battery modules for storing electrical power. An integrated controller is electrically and communicatively coupled with the power source for monitoring and controlling the power source to provide electrical power to aircraft subsystems. A mobile device is communicatively coupled with the integrated controller for communicating instructions to the integrated controller for initiating preflight readiness of the aircraft and for monitoring preflight readiness. A method for preconditioning an aircraft includes determining a state-of-charge of an APU and activating an environmental control subsystem for preconditioning the aircraft by adjusting a current temperature according to a preconditioning profile based on one or more of a target temperature, a target time, the current temperature, an outside air temperature, an amount of energy, and a state-of-charge of the APU.

公开(公告)号：USD915968S1

公开(公告)日：2021-04-13

申请号：US29623856

申请日：2017-10-27

Applicant: Textron Aviation Inc.

Designer： Michael Scott Robinson ,  Joshua Phillip DeDonder ,  Todd Alan Thisius

公开(公告)号：US10974843B2

公开(公告)日：2021-04-13

申请号：US15927248

申请日：2018-03-21

Applicant: Textron Aviation Inc.

Inventor： Vernon Weng-Yew Chang ,  Charles Bernard Beuning ,  August Bryce Ratzlaff ,  David Lee Swartzendruber

IPC: B64D41/00 ,  H02J1/00 ,  B64D13/06 ,  H02J7/00 ,  G05D1/00 ,  H01M2/10 ,  H02M7/44 ,  H02J7/14 ,  B64F5/40 ,  H02J1/10 ,  B64F5/60 ,  B64D45/00 ,  G01F9/00 ,  G07C5/00 ,  H01M10/42 ,  H01M2/30 ,  H01M2/20

Abstract: A distributed auxiliary-power-unit (APU) system for an aircraft includes one or more battery modules for storing electrical power, and a plurality of racks distributed throughout the aircraft for receiving the one or more battery modules to electrically connect with an electrical subsystem of the aircraft. A plurality of hot-swappable racks are adapted to receive the battery modules for electrically and communicatively coupling with the electrical subsystem and an integrated controller. A remote interface is communicatively coupled with the integrated controller for receiving user-input to direct electrical power from the battery modules to one or more subsystems of the aircraft. A number of battery modules installed is based on an amount of electrical power planned for a given flight of the aircraft.