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    FORCE ABSORBING SHOULDER BELT ASSEMBLIES ESPECIALLY USEFUL FOR AIRCRAFT OCCUPANT SEATS
    61.
    发明申请
    FORCE ABSORBING SHOULDER BELT ASSEMBLIES ESPECIALLY USEFUL FOR AIRCRAFT OCCUPANT SEATS 有权

    公开(公告)号：US20250100690A1

    公开(公告)日：2025-03-27

    申请号：US18472142

    申请日：2023-09-21

    Applicant: Textron Aviation Inc.

    Inventor： Dean Ross GONZALEZ

    IPC: B64D11/06

    Abstract: Force absorbing shoulder belt assemblies for vehicle seats, especially aircraft seats, are provided. The shoulder belt assemblies will include a box structure defining an interior space having an open rear end and adapted to being fixed to adjacent vehicle structure, a block of a compressible material positioned within the interior space of the box structure, a rear plate in pressing contact with the rear face of the block of compressible material, and an inertial reel assembly carried by the rear plate and including a shoulder web strap which extends through the rear plate, the block of compressible material and the box structure. When a deceleration force of predetermined magnitude is exerted on the shoulder web strap of the inertial reel, the rear plate will responsively be forcibly pressed against the block of compressible material thereby compressively crushing the compressible material within the box structure to thereby absorb shock force of the shoulder web strap against vehicle seat occupant's torso.

    Aircraft Heated Seat
    63.
    发明申请
    Aircraft Heated Seat 有权

    公开(公告)号：US20250058877A1

    公开(公告)日：2025-02-20

    申请号：US18450843

    申请日：2023-08-16

    Applicant: Textron Aviation Inc.

    Inventor： David Wayne Davis ,  Joshua Lawrence Bell

    IPC: B64D11/06

    Abstract: A heated seat for an aircraft includes a heating element disposed on a cushioning material and overlayed by an upholstery. The heating element includes a flexible base and a plurality of thin and flexible heating coils that conform to the seat shape such that no cushioning material is applied between the heating element and the upholstery. By providing direct contact between the heating element and the upholstery, smaller heating elements requiring less electrical power may be used to sufficiently heat the seat compared with traditional heating elements.

    Engine isolation subframe for aircraft
    64.
    发明授权
    Engine isolation subframe for aircraft 有权

    公开(公告)号：US12221218B2

    公开(公告)日：2025-02-11

    申请号：US18153225

    申请日：2023-01-11

    Applicant: Textron Aviation Inc.

    Inventor： Rory Derik Cooper ,  Travis Elliot Smith

    IPC: B64D27/40 ,  B64D27/20

    Abstract: An engine vibration isolation subframe for aircraft includes a forward frame and a forward beam connected to the forward frame. The forward beam includes a first end configured to connect to a first engine and a second end configured to connect to a second engine. An aft frame is disposed aft of the forward frame and includes a first aft beam connected to the aft frame and the first engine and a second aft beam connected to the aft frame and the second engine, where the second aft beam is disposed substantially opposite the first aft beam. At least one forward isolator assembly is connected to the forward frame and at least one aft isolator assembly is connected to the aft frame.

    Hybrid Flight Control System
    67.
    发明申请
    Hybrid Flight Control System 有权

    公开(公告)号：US20240409203A1

    公开(公告)日：2024-12-12

    申请号：US18737093

    申请日：2024-06-07

    Applicant: Textron Aviation Inc.

    Inventor： Stephen M. Eddy ,  Steven G. Hagerott

    IPC: B64C13/50 ,  B64C13/04

    Abstract: A hybrid flight control system includes an operator input device having a force sensor and/or a position sensor. The operator input is connected to a first portion of the control surface via a mechanical linkage. The system includes an electro-mechanical actuator and an electro-mechanical actuator control system in data communication with the electro-mechanical actuator, as well as a flight control computing system in data communication with the operator input device and the electro-mechanical actuator control system. Upon receiving an input from an operator, the operator input device sends a signal to the flight control computing system. Upon receiving a signal from the operator input device, the flight control computing system sends a signal to the electro-mechanical actuator control system. Upon receiving a signal from the electro-mechanical actuator control system, the electro-mechanical actuator moves a second portion of the control surface according to a predetermined set of conditions.

    Aircraft vanity display screen
    69.
    外观设计
    Aircraft vanity display screen 有权

    公开(公告)号：USD1044652S1

    公开(公告)日：2024-10-01

    申请号：US29871646

    申请日：2023-02-24

    Applicant: Textron Aviation Inc.

    Designer： Frank Joseph Rowe ,  Jonathan Lynn Headrick ,  Joshua Lawrence Bell ,  Matthew R. Harrell

    Abstract: FIG. 1 is a perspective view of an aircraft vanity display screen showing our new design in an aircraft lavatory;
    FIG. 2 is another perspective view showing the aircraft vanity display screen of FIG. 1;
    FIG. 3 is a side view showing the aircraft vanity display screen of FIG. 1;
    FIG. 4 is another side view showing the aircraft vanity display screen of FIG. 1; and,
    FIG. 5 is front view showing the aircraft vanity display screen of FIG. 1.
    In FIGS. 1-5, broken lines indicate environmental structure that forms no part of the claimed design.

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