公开(公告)号：US20230266216A1

公开(公告)日：2023-08-24

申请号：US17678808

申请日：2022-02-23

Applicant: Bell Textron Inc.

Inventor： Louis CHARRON ,  Maxime LAPALME ,  Daniel DEL ROSSI ,  Alexis DUGRÉ

IPC: G01N3/20 ,  G01M5/00

CPC classification number: G01N3/20 ,  G01M5/0016 ,  G01N2203/0073

Abstract: An apparatus for introducing a test load to a rotor blade test specimen for fatigue testing includes a body extending along a longitudinal axis in a first direction from a first end to a second end, and the body having an internal cavity with an opening at the second end configured to dispose a tip portion of the rotor blade test specimen.

公开(公告)号：US20230211868A1

公开(公告)日：2023-07-06

申请号：US17569167

申请日：2022-01-05

Applicant: Bell Textron Inc.

Inventor： Michael Ross Wilkinson ,  James Everett Kooiman ,  Clegg Benjamin Brian Smith ,  Jeffrey Matthew Williams ,  Tjepke Heeringa ,  David G. Carlson

IPC: B64C1/24

CPC classification number: B64C1/24

Abstract: A folding step system includes a housing forming an interior space and a step comprising a step surface. The step is movable between a stowed configuration in which substantially all of the step surface is disposed within the interior space and a deployed configuration in which at least a portion of the step surface is disposed outside of the interior space and at least a portion of the step surface is disposed within the interior space.

公开(公告)号：US11691753B2

公开(公告)日：2023-07-04

申请号：US17095634

申请日：2020-11-11

Applicant: Bell Textron Inc.

Inventor： Jeffrey Paul Nissen ,  Troy Cyril Schank ,  Brent Chadwick Ross ,  Steven Ray Ivans

IPC: B64D39/04 ,  B64D7/00 ,  B64D39/02

CPC classification number: B64D39/04 ,  B64D7/00 ,  B64D39/02

Abstract: An aerial resupply system (ARS) including a supply aircraft. The supply aircraft includes at least one of supply fuel, an ordinance, and data. The supply aircraft also includes a retractable boom system (RBS) configured for selective stowage within a fuselage of the supply aircraft and configured to supply at least one of supply fuel, the ordinance, and data to a location external to the fuselage.

公开(公告)号：US20230194312A1

公开(公告)日：2023-06-22

申请号：US17555104

申请日：2021-12-17

Applicant: Bell Textron Inc.

Inventor： Kyle Thomas Cravener ,  Patrick Smith ,  Troy Cyril Schank ,  Brady Garrett Atkins ,  Kynn Jerald Schulte

IPC: G01D5/16

CPC classification number: G01D5/16 ,  B64C27/39

Abstract: A rotor-hub-flap anisotropic-sensor system includes a rotor hub, a plurality of anisotropic-sensor arrangements interoperably coupled to the rotor hub and operable to measure flapping of the rotor hub, a plurality of rotor blades connected to the rotor hub, and at least one flight control computer interoperably coupled to the plurality of anisotropic-sensor arrangements.

公开(公告)号：US20230192286A1

公开(公告)日：2023-06-22

申请号：US17558263

申请日：2021-12-21

Applicant: Bell Textron Inc.

Inventor： Steven R. Ivans ,  Berlin B. Benfield ,  Brent C. Ross

IPC: B64C27/52 ,  B64C29/00

CPC classification number: B64C27/52 ,  B64C29/0033

Abstract: There is disclosed in one example a tiltrotor system for a vertical takeoff and landing (VTOL) aircraft, including: a rotor pylon, wherein the rotor pylon is rotatable, via a rotation maneuver, between a substantially horizontal orientation and a substantially vertical orientation; a linear actuator disposed to actuate the rotation maneuver; and a mechanical guide disposed to maintain a center of gravity along a substantially linear axis throughout the rotation maneuver.

公开(公告)号：US11643186B2

公开(公告)日：2023-05-09

申请号：US16679121

申请日：2019-11-08

Applicant: Bell Textron Inc.

Inventor： Karl Schroeder ,  William Anthony Amante ,  Joseph Richard Carpenter, Jr. ,  Christopher Marion Johnson

IPC: B64D27/26 ,  B64C11/00 ,  B64C11/46 ,  B64C11/02 ,  B64C29/00

CPC classification number: B64C11/001 ,  B64C11/02 ,  B64C11/46 ,  B64D27/26 ,  B64C29/0033 ,  B64D2027/264

Abstract: A duct for a ducted-rotor aircraft may include internal structural components such as a spindle that is supported by a fuselage of the aircraft, first and second annular spars that are attached to an end of the spindle, a central hub that supports a motor of the aircraft, a plurality of stators that extend from the central hub to the second spar, and a plurality of ribs that are attached to the first spar and the second spar at respective opposed ends. The spindle may include an attachment interface to which the first and second spars are attached. The attachment interface may be disposed at the second end of the spindle. The attachment interface may define first and second arc-shaped planar surfaces to which the first and second spars, respectively, are attached.

公开(公告)号：US11634216B2

公开(公告)日：2023-04-25

申请号：US17036798

申请日：2020-09-29

Applicant: Bell Textron Inc.

Inventor： William Anthony Amante ,  Timothy Brian Carr

IPC: B64C29/00 ,  B64C11/00 ,  B64C27/20

Abstract: In an embodiment, a ducted fan assembly includes a housing that further includes a rotor. The ducted fan assembly also includes a plurality of stators that extend outward from the housing. The ducted fan assembly also includes a control vane pivotally attached to at least one of the plurality of stators. The ducted fan assembly also includes a rim that extends around at least a portion of a perimeter of the ducted fan assembly and is supported by the plurality of stators and the control vane, where the rim defines an opening surrounding at least a portion of the housing.

公开(公告)号：US20230118750A1

公开(公告)日：2023-04-20

申请号：US17503736

申请日：2021-10-18

Applicant: Bell Textron Inc.

Inventor： Bryan Kenneth Baskin ,  Kyle Thomas Cravener ,  Andrew Ryan Maresh

IPC: B64C27/32 ,  B64C29/00

Abstract: A teeter flap lock for an aircraft may include at least one pair of diametrically positioned teeter flap lock plates extending from a rotor teetering hinge, spaced apart from a rotor mast of the aircraft. A teeter flap lock block is positioned about the rotor mast and is configured to fit between the teeter flap lock plates and the rotor mast. The teeter flap lock block fits between and contacts the teeter flap lock plates in an engaged position, and is movable between the engaged position and a disengaged position relative to the teeter flap lock plates. The teeter flap lock enables flapping of rotors coupled to the rotor mast via the teetering hinge when the teeter flap lock block is in the disengaged position and disables flapping of the rotors when the teeter flap lock block is in the engaged position.

公开(公告)号：US20230114485A1

公开(公告)日：2023-04-13

申请号：US17498473

申请日：2021-10-11

Applicant: Bell Textron Inc.

Inventor： Brian Edward Tucker ,  Matthew Curtis Ledbetter ,  Silvio Mario Lopez ,  Drew Franklin Waller ,  Jobin J. Thomas

IPC: B64D45/00 ,  G01M15/05 ,  G01M17/00 ,  G07C5/00

Abstract: A system and method for reducing data noise for vehicle monitoring sensors using parameter-based correction, the system including An embodiment system includes a sensor operable to make a sensor reading and generate a sensor signal, and a data server operable to acquire a condition indicator model correlating operational parameters with condition indicators, and to acquire a current condition indicator according to the sensor signal, the data server further operable to generate an adjusted condition indicator by adjusting the current condition indicator according to the condition indicator model, and to determine whether an alert condition is indicated, according to at least the adjusted condition indicator, by a condition indicator set that includes the adjusted condition indicator, and to provide an alert in response to determining that the alert condition is indicated.

公开(公告)号：US11618588B2

公开(公告)日：2023-04-04

申请号：US17069413

申请日：2020-10-13

Applicant: Bell Textron Inc.

Inventor： Scott David Poster ,  Martin Peryea

IPC: B64C25/56 ,  B64C27/06 ,  B64F1/22

Abstract: The present invention includes an apparatus for preventing aircraft rollover upon a water landing comprising: a deployable first and/or second boom affixed by a first end to the aircraft and capable of deployment substantially perpendicular to a longitudinal axis of the aircraft; and a first and/or second air bladder attached to a second end of the first and/or second boom, wherein the first and/or second air bladders are configured to inflate when an aircraft lands in the water, wherein deployment of the first and second boom and air bladder prevents aircraft rollover upon water landing; or a deployable keel affixed by a first end to the aircraft and capable of deployment substantially perpendicular to a longitudinal axis and opposite a rotor of the aircraft upon a water landing, wherein the keel is sized to prevent aircraft rollover upon deployment; or both.