公开(公告)号：US20200216179A1

公开(公告)日：2020-07-09

申请号：US16719525

申请日：2019-12-18

Applicant: Textron Aviation Inc.

Inventor： Brent William Last ,  Gregory Lynn Ellis ,  Brandon Riley Shannon

IPC: B64D11/06 ,  A47C7/50

Abstract: An upholstery-guided footrest includes a footrest mechanically coupled to a seat. The footrest is configured for moving between a stowed position and one or more deployed positions. A flexible member has a first end and a second end opposite the first end. The first end is fastened to the seat and the second end is fastened to the footrest such that the flexible member supports the footrest during stowing. The flexible member bends around a frontside of the seat and is configured to guide and support the footrest into a stowed position.

公开(公告)号：US10689120B2

公开(公告)日：2020-06-23

申请号：US15689301

申请日：2017-08-29

Applicant: Textron Aviation Inc.

Inventor： Thang Chien Phi

IPC: B64D11/06 ,  B60N2/14 ,  B60N2/30

Abstract: A stowable reversible seat for a vehicle includes a first member pivotally coupled to a floor for supporting a seat base, a second member releasably secured to the floor for supporting the seat base, and a seat back pivotally coupled to the first member. Components of the seat pivot between a folded configuration for stowing and a deployed configuration for seating. The orientation of the seat may be reversed for switching between a forward-facing direction and an aft-facing direction. A method of configuring a seat into an aircraft includes adapting a cabinet area to receive and conceal the seat, configuring a rail to make the seat slidable out from the cabinet area into an aisle, attaching a pivotable seat base on the seat, and pivotally mounting a supporting leg underneath a portion of the seat to secure the pivotable seat base in a substantially horizontal position.

公开(公告)号：US20200182177A1

公开(公告)日：2020-06-11

申请号：US16707567

申请日：2019-12-09

Applicant: Textron Aviation Inc.

Inventor： Mark Sheridan Hunter ,  Ronald J. Parker

IPC: F02D41/02 ,  F02D11/02 ,  F02D11/10 ,  F16H59/02 ,  B64D31/04 ,  B64D31/14 ,  F02D41/14

Abstract: Disclosed is a throttle quadrant arrangement utilizing a throttle lever mechanically connected to three Rotary Variable Differential Transformers (RVDTs). The signals from the RVDTs are monitored by a process where the processing component. More specifically, RVDT outputs are monitored by the engine control system to determine if they are outside a predetermined range of operability. If an RVDT is not operable, the engine control system establishes a thrust output using the signal from one of the functional two. If only one or none are within the range, the system moves on to a default mode.

公开(公告)号：US20190283861A1

公开(公告)日：2019-09-19

申请号：US16298009

申请日：2019-03-11

Applicant: Textron Aviation Inc.

Inventor： Raymond Charters Maple

IPC: B64C7/02 ,  B64C21/02

Abstract: A fluid diverting air inlet includes an intake opening through an outer surface of an enclosure for receiving air flowing outside the outer surface. The intake opening ramps downwardly below the outer surface to define an intake passageway. An air diversion device is formed by lateral sidewalls of the intake opening that extend vertically above the outer surface. The lateral sidewalls converge together at an upstream end of the air inlet, and the lateral sidewalls diverge apart towards a downstream end of the air inlet. Flanges extend outwardly from the tops of the lateral sidewalls such that divided air passageways for boundary layer fluids are formed on each side of the air diversion device. The sidewalls and flanges are integrated with the air inlet such that fluid moving immediately adjacent the outer surface of the enclosure is diverted around the air inlet to avoid ingestion into the intake opening.

公开(公告)号：US10300896B2

公开(公告)日：2019-05-28

申请号：US15479512

申请日：2017-04-05

Applicant: Textron Aviation Inc.

Inventor： Darrin Michael Jones ,  Michael Troy Heeren ,  Dennis Stephen Bradfield

IPC: B60T8/88 ,  B60T8/17 ,  B60T7/12 ,  B60T7/04 ,  B60T13/74 ,  B60T8/00 ,  B60T13/66 ,  B60T17/18 ,  B60T8/32

Abstract: Disclosed is a brake system for aircraft that uses a control unit that is configured to control actuators at each wheel using one channel operating an associated brake control module, and other actuators at the same wheel using a second module operated completely independently using a second module. The use of the first and second groups of actuators are alternated periodically, e.g., for each flight.

公开(公告)号：US20180273197A1

公开(公告)日：2018-09-27

申请号：US15927241

申请日：2018-03-21

Applicant: Textron Aviation Inc.

Inventor： Vernon Weng-Yew Chang ,  Charles Bernard Beuning ,  Adam Blake Wolfe

IPC: B64D41/00 ,  B64D13/06 ,  H02J7/00 ,  H02M7/44 ,  G05D1/00

CPC classification number: B64D41/00 ,  B64D13/06 ,  B64D45/00 ,  B64D2013/0611 ,  B64D2041/002 ,  B64D2045/0085 ,  B64D2221/00 ,  B64F5/40 ,  B64F5/60 ,  G01F9/001 ,  G05D1/0011 ,  G07C5/008 ,  H01M2/1077 ,  H01M2/20 ,  H01M2/30 ,  H01M10/425 ,  H01M2010/4271 ,  H01M2220/20 ,  H02J1/00 ,  H02J1/10 ,  H02J7/0063 ,  H02J7/007 ,  H02J7/1423 ,  H02M7/44 ,  Y02T50/44 ,  Y02T50/56

Abstract: An auxiliary power unit (APU) for aircraft is provided. The APU includes one or more battery modules for storing electrical power and an integrated controller adapted to operate the one or more battery modules for electrically powering aircraft subsystems for preflight readiness. A remote interface is communicatively coupled with the integrated controller and is adapted for displaying data from the APU and for receiving user instructions for transmission to the integrated controller for governing flow of electrical current between the APU and the aircraft subsystems.

公开(公告)号：US20180116391A1

公开(公告)日：2018-05-03

申请号：US15799607

申请日：2017-10-31

Applicant: Textron Aviation Inc.

Inventor： Jason Michael Decker ,  Michael Scott Robinson ,  Christopher Adair Pinkerton

IPC: A47B1/05 ,  B64D11/06

CPC classification number: B64D11/064 ,  A47B1/05 ,  A47B13/023 ,  A47B83/00 ,  A47B85/04 ,  A47B85/08 ,  A47B2001/053 ,  B64D11/0601 ,  B64D11/0605 ,  B64D11/0627

Abstract: A system and method for providing a table in aircraft is disclosed. The table is able to be deployed out such that it extends across an aisle towards an inwardly-facing seat on the other side. The extension enables passengers sitting in the side facing seat to support articles and otherwise use the extended surface area.

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.