公开(公告)号：US20250044915A1

公开(公告)日：2025-02-06

申请号：US18784887

申请日：2024-07-25

Applicant: Textron Aviation Inc.

Inventor： Joshua Lawrence Bell ,  Stephen Howard Fagan ,  Michael Scott Robinson ,  Matthew R. Harrell

IPC: G06F3/0482 ,  B64D11/00 ,  G06F3/0484 ,  H04N7/18

Abstract: A curved screen skylight for an aircraft includes a curved display screen which is configured to display imagery provided from a camera positioned on the aircraft or preloaded imagery stored on a memory storage device. The curved screen display conforms to an aircraft overhead panel and can be secured using flanges extending from the overhead panel.

公开(公告)号：USD1045437S1

公开(公告)日：2024-10-08

申请号：US29871175

申请日：2023-02-14

Applicant: Textron Aviation Inc.

Designer： Jason Michael Decker ,  Lydia P. Pierce ,  Stephen Howard Fagan ,  Merril Binford Williams

Abstract: FIG. 1 is a perspective view of the cabin floor showing our new design in an environment of use in an aircraft cabin with seats removed;
FIG. 2 is a perspective view of the cabin floor of FIG. 1 shown in an environment of use in an aircraft cabin with seats removed;
FIG. 3 is a top view of the cabin floor of FIG. 1 shown in an environment of use in an aircraft cabin with seats removed;
FIG. 4 is a top view of the cabin floor of FIG. 1 shown with the environment removed for clarity of disclosure;
FIG. 5 is a perspective view of the cabin floor of FIG. 1 shown with the environment removed for clarity of disclosure; and,
FIG. 6 is another perspective view of the cabin floor of FIG. 1 shown with the environment removed for clarity of disclosure.
In FIGS. 1-6, broken lines indicate environmental structure that forms no part of the claimed design.

公开(公告)号：US20230288020A1

公开(公告)日：2023-09-14

申请号：US18180627

申请日：2023-03-08

Applicant: Textron Aviation Inc.

Inventor： Michael John Seibel ,  Stephen Howard Fagan

IPC: F16M13/02 ,  F16M11/10 ,  F16M11/20

CPC classification number: F16M13/02 ,  F16M11/105 ,  F16M11/2021 ,  F16M2200/022

Abstract: Disclosed is an electronics device holder made to be mountable on an aircraft control stick arrangement. The holder enables two dimensions of rotation. Rotation clockwise and counterclockwise is provided by a disk on which the holder is mounted. The disk edges are trapped underneath a containing plate. Friction enables the disk, and thus, the holder to be held in different circular positions. A friction hinge is used to establish and hold different pitch positions for the electronics device.

公开(公告)号：US20220089288A1

公开(公告)日：2022-03-24

申请号：US17476924

申请日：2021-09-16

Applicant: Textron Aviation Inc.

Inventor： Paul Stokholm Warren ,  Stephen Howard Fagan

IPC: B64D11/06

Abstract: A powered seat-base release system includes a rod rotatably mounted in a bucket assembly of an aircraft seat and a motor mechanically coupled to the rod. The motor is configured for rotating the rod from a locked position to a released position. A locking mechanism is configured for preventing motion of the bucket assembly. A cable has a first end and a second end, the first end being mechanically coupled to the rod, and the second end being mechanically coupled to the locking mechanism. A user interface is configured to activate the motor for rotating the rod to the released position such that the rod pulls the cable thereby releasing the locking mechanism to enable motion of the bucket assembly. Upon deactivation of the motor, a biasing mechanism is configured to counter rotate the rod from the released position to the locked position thereby back driving the motor.

公开(公告)号：US20200148366A1

公开(公告)日：2020-05-14

申请号：US16660192

申请日：2019-10-22

Applicant: Textron Aviation Inc.

Inventor： Stephen Howard Fagan ,  Paul Stokholm Warren ,  Emily O'Kelley Pearson ,  Jeremy Joseph Kneuper ,  Phillip Kendrick

IPC: B64D11/06

Abstract: A seat base includes a plurality of linear actuators each having a first end pivotally mounted to a base member and a second end pivotally mounted to a seat member. A controller is adapted for controlling an extension length of each of the plurality of linear actuators in a coordinated manner for adjusting a position of the seat member with six degrees-of-freedom and for damping vibration of the seat member. An active vibration mitigation method for reducing vibrations of an aircraft seat includes receiving vibration data from one or more accelerometers mounted to the aircraft seat and determining a vibration profile based on the vibration data. When vibration mitigation is warranted, control signals for damping vibration are determined and transmitted to a plurality of linear actuators adapted to support the aircraft seat.