公开(公告)号：US20250156323A1

公开(公告)日：2025-05-15

申请号：US18936562

申请日：2024-11-04

Applicant: Textron Aviation Inc.

Inventor： Adam Blake Wolfe ,  Haines Todd ,  Mark Christopher Hansen

IPC: G06F12/0802 ,  B64D45/00

Abstract: Systems and methods are disclosed for providing performant, pre-initialization data caching for capturing faults during aircraft recording system startup and writing to one or more local caches an aircraft recording system (ARS) device. One or more candidate input parameter values are captured upon power up of the aircraft recording system, the one or more candidate input parameter values associated with one or more aircraft input parameters corresponding to one or more aircraft system controls. The one or more candidate input parameter values may not have been capable of being captured prior to a full aircraft recording system initialization. An external embedded data processing system is initialized, and upon successful initialization locally cached pre-initialization aircraft data is retrieved and stored in combination with subsequently-acquired aircraft data. The one or more candidate input parameter values may be one or more fault conditions associated with the aircraft.

公开(公告)号：US20250145277A1

公开(公告)日：2025-05-08

申请号：US18504662

申请日：2023-11-08

Applicant: Textron Aviation Inc.

Inventor： Gavin SMITH ,  David M. VALLADE

IPC: B64C19/00 ,  F16B21/12 ,  F16C13/00

Abstract: Double flanged clevis pins are provided in aircraft flight control pulley systems and are mounted between the opposed side walls of the pulley mounting bracket at a closely spaced separation distance relative to a respective pulley and the cable retained within the pulley groove. The outboard facing surface of each of the clevis pin flanges is positioned in abutting relationship with an adjacent inboard facing surface portion of a respective one of the opposed side walls of the mounting bracket while outboard ends of the clevis pin extend coaxially outwardly therefrom and through the adjacent mounting bracket side wall. The central pin section of the clevis pin is therefore closely spaced above an adjacent portion of the circumferential edge of the pulley in which an aircraft control cable is received. Such an assembly thereby serves to maintain the control cable within the pulley groove and prevents one or both of the bracket side walls from being deformed over time that may in turn undesirably chafe the control cable.

公开(公告)号：US12264518B2

公开(公告)日：2025-04-01

申请号：US18354239

申请日：2023-07-18

Applicant: Textron Aviation Inc.

Inventor： Michael Clinton Lay ,  Evan M. Johnson ,  Isaac Anthony Hoetmer ,  Joel Allen Pegg ,  Edward Donald Harrison

IPC: B64C1/14 ,  E05B41/00 ,  E05B85/10 ,  E05C17/32 ,  E05F1/10

Abstract: An escape hatch stay system for an aircraft and methods of using the escape hatch stay system. An escape hatch stay system includes a first stop arm, a second stop arm, and a gas strut. The first stop arm is rotatably coupled to the second stop arm, and the second stop arm is pivotably coupled to the gas strut. The first and second stop arms are lockable to preclude relative movement therebetween to lock the escape hatch in an open position. When the escape hatch is in the open position, the escape hatch may not be closed shut without manual intervention. When the escape hatch is in the open position, a load applicable to push the escape hatch open past the open position is damped by the gas strut.

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.

公开(公告)号：US20250058878A1

公开(公告)日：2025-02-20

申请号：US18449124

申请日：2023-08-14

Applicant: Textron Aviation, Inc.

Inventor： Matthew William Reese ,  Jason Michael Decker ,  Adam Ryan Payton

IPC: B64D11/06 ,  B64D11/00

Abstract: A system for storage includes a drawer configured to open with a push, a drawer base, and a seat. A drawer face of the drawer is free of a handle. The drawer opens in a first direction along two or more slides. The drawer base is under the drawer, the drawer being coupled to the drawer base. The seat is over the drawer. The seat faces perpendicular to the first direction.

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.

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.

公开(公告)号：USD1055839S1

公开(公告)日：2024-12-31

申请号：US29870462

申请日：2023-01-27

Applicant: Textron Aviation Inc.

Designer： Karen Tamasi Cooper ,  Merril Binford Williams

公开(公告)号：USD1055833S1

公开(公告)日：2024-12-31

申请号：US29871947

申请日：2023-03-02

Applicant: Textron Aviation Inc.

Designer： Frank Joseph Rowe ,  Merril Binford Williams

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.