公开(公告)号：US10976751B1

公开(公告)日：2021-04-13

申请号：US15828795

申请日：2017-12-01

Applicant: Textron Aviation Inc.

Inventor： Steven G. Hagerott ,  Russell Peters ,  Stephen M. Eddy

IPC: G05D1/08 ,  G05D1/10 ,  G05B23/02 ,  B64C13/16 ,  G05D1/00

Abstract: A method for monitoring an oscillatory signal from an oscillating device includes filtering the oscillatory signal to within a desired frequency band to provide a filtered signal and extracting an amplitude from the filtered signal. The method further includes switching control of the oscillating device when the amplitude exceeds a predetermined amplitude requirement for a predetermined duration. An oscillatory signal monitor includes a first controller and a second controller each configured to independently control an oscillating device. An oscillatory signal based on a position of the oscillating device is filtered to a desired frequency band, and an amplitude is extracted from the filtered signal. A switch is provided for switching control of the oscillatory device from the first controller to the second controller when the amplitude exceeds a predetermined amplitude requirement for a predetermined duration.

公开(公告)号：US10969796B2

公开(公告)日：2021-04-06

申请号：US16196485

申请日：2018-11-20

Applicant: Textron Aviation Inc.

Inventor： Steven G. Hagerott

IPC: G05F1/08 ,  G05D1/08

Abstract: An autopilot nonlinear compensation method includes providing an autopilot command for executing an aircraft maneuver, determining a desired aerodynamic moment of the aircraft based on the autopilot command, providing a measured pilot interface position, determining a total aerodynamic moment of the aircraft based on the measured pilot interface position and the autopilot command in combination with the desired aerodynamic moment, determining a ratio of the desired aerodynamic moment to the total aerodynamic moment, and adjusting the autopilot command with a corrective command based on the ratio. The method may be used to stabilize autopilot control of an aircraft following nonlinear deployment of a control surface.

公开(公告)号：US10800112B2

公开(公告)日：2020-10-13

申请号：US15702068

申请日：2017-09-12

Applicant: Textron Aviation Inc.

Inventor： Phillip Anthony Kendrick ,  Lawrence Arthur Gintert ,  Herbert Lee Skidmore ,  Mike Preston McKown

IPC: B29C65/00 ,  B29C65/48 ,  B29C65/60 ,  B29C37/00 ,  B32B7/05 ,  B32B7/08 ,  B32B7/14 ,  B32B37/00 ,  B32B3/30 ,  B32B37/12 ,  B29C70/30 ,  B33Y80/00 ,  B33Y10/00 ,  B29C35/02 ,  B29K101/12 ,  B29L31/30

Abstract: A system and process for bonding involves a pocket made into one article is used to secure that article to another using a flowable, curable material (e.g., resin) which during saturation enters through a passageway and at least partially fills the void. When the article is cured, the article is bonded to another article to which resin has also been applied since the void (now containing cured material) is larger than the passageway.

公开(公告)号：US10746378B2

公开(公告)日：2020-08-18

申请号：US15717412

申请日：2017-09-27

Applicant: Textron Aviation Inc.

Inventor： Timothy James Bachman ,  Joseph Allan Smarsh

IPC: F21V8/00 ,  F21V14/00 ,  G02B6/00 ,  B64D45/00 ,  F21S19/00 ,  F21V14/08 ,  G08B5/00 ,  E05B41/00 ,  B64C1/14 ,  E05B17/10

Abstract: A mechanical state indicator system concealed within an enclosure includes a light source for providing light and multiple light paths coupled to the light source for directing the light. Each of the light paths includes a gap configured to receive a mechanical state indicator rigidly coupled to a mechanism. Movement of the mechanism between a first state and a second state moves the mechanical state indicator into and out of the gap. Readouts are coupled to each of the light paths for displaying an indication of mechanical state based on a position of a respective mechanical state indicator. The readouts are co-located for collective viewing.

公开(公告)号：US20190323539A1

公开(公告)日：2019-10-24

申请号：US16379974

申请日：2019-04-10

Applicant: Textron Aviation Inc.

Inventor： Brent Clothier

IPC: F16B33/00 ,  B64C3/34

Abstract: An integral sealant O-ring for sealing fasteners in mating surfaces of a fuel tank includes a fastener hole through an inner mating surface and an outer mating surface, the fastener hole has a chamfer along a fay interface between the mating surfaces. A layer of sealant is applied along the fay interface, and upon tightening of the fastener, the inner and outer mating surfaces are pulled together squeezing the sealant into the chamfer and forming an integral sealant O-ring around the fastener. A method of forming an integral sealant O-ring includes forming a chamfer in a first mating surface substantially concentric with a fastener hole, applying a layer of sealant along the first mating surface, pulling together the first mating surface with a second mating surface by tightening a fastener to trap sealant within the chamfer for forming an integral sealant O-ring.

公开(公告)号：US10349489B2

公开(公告)日：2019-07-09

申请号：US15795786

申请日：2017-10-27

Applicant: Textron Aviation Inc.

Inventor： Michael Scott Robinson ,  Frank Joseph Rowe ,  Todd Alan Thisius

IPC: H05B37/02 ,  B64C1/14 ,  B64D11/00 ,  F21V14/00 ,  G02F1/133 ,  G02F1/1334 ,  F21V23/00 ,  E04D13/03 ,  F21S10/02 ,  F21Y115/10 ,  F21S11/00 ,  F21W121/00 ,  F21Y113/13

Abstract: An adaptable skylight includes a frame facing an interior of an enclosure having an opening for allowing light to pass. An opacity-control pane adjacent the opening allows a variable amount of light to pass, and an artificial light source illuminates the frame. An aircraft skylight assembly includes a variable pane, an artificial light source for illuminating portions of the skylight assembly, and a controller configured for adjusting an amount of external light transmission through the variable pane and an amount of artificial light illumination. An internal ambiance lighting system includes the adaptable skylight having a dimmable pane for providing transmission of a variable amount of external light into an enclosure, the artificial light illuminates the frame surrounding the adaptable skylight, and the controller automatically adjusts external light transmission through the adaptable skylight and illumination of the frame based on a lighting preference.

公开(公告)号：US20180273211A1

公开(公告)日：2018-09-27

申请号：US15978518

申请日：2018-05-14

Applicant: Textron Aviation Inc.

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

IPC: B64F5/60 ,  G01F9/00 ,  B64D45/00 ,  G07C5/00

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：US20180273209A1

公开(公告)日：2018-09-27

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: B64F5/60 ,  G07C5/00 ,  G01F9/00 ,  B64D45/00

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 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：US20180169954A1

公开(公告)日：2018-06-21

申请号：US15847087

申请日：2017-12-19

Applicant: Textron Aviation Inc.

Inventor： Phillip Anthony Kendrick ,  Lawrence Arthur Gintert ,  Michael Preston McKown

IPC: B29C64/393 ,  B29C64/40 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y50/02

CPC classification number: B29C64/393 ,  B29C64/40 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y50/02 ,  G06F17/50

Abstract: An additive manufacturing method for improved core structure includes splitting a computational model into sequentially queued individual model segments based on a predetermined number of slices with a predetermined orientation, and building a part in layers applied sequentially to form a final part having a core portion supported with a custom in-fill pattern. An additive manufacturing system for providing an improved core structure supported by a custom in-fill pattern includes a controller having instructions for individual model segments based on slices of a solid model, and a 3D printer for sequentially printing individual model segments in adjacent layers. A 3D-printed part includes a first exterior surface separated by a gap from a second exterior surface, and an internal core structure within the gap for mechanically connecting the first exterior surface to the second exterior surface. The internal core structure includes a custom in-fill pattern of support members.

公开(公告)号：US20180162532A1

公开(公告)日：2018-06-14

申请号：US15824309

申请日：2017-11-28

Applicant: Textron Aviation Inc.

Inventor： David James Swanson ,  Michael Allen Bullard ,  Phillip Anthony Kendrick

IPC: B64D11/04

CPC classification number: B64D11/04

Abstract: A multi-rail galley includes a countertop on top of a first storage portion, and a second storage portion above the countertop. The countertop includes a first plurality of rails on a top surface that are configured for receiving at least one countertop insert. The second storage portion has a second plurality of rails beneath a bottom surface of the second storage portion and configured for receiving at least one hanging insert. A method of providing a customizable aircraft galley includes providing a countertop above a storage compartment, the countertop having a horizontal surface facing upwards with a plurality of rails disposed on top of the horizontal surface, installing a galley insert onto one of the plurality of rails via a matching slot in the galley insert, and removing the galley insert from one of the plurality of rails, enabling stowage of the galley insert.