公开(公告)号：US10583916B2

公开(公告)日：2020-03-10

申请号：US16401332

申请日：2019-05-02

Applicant: Bell Helicopter Textron Inc.

Inventor： Kyle Thomas Cravener ,  Brady Garrett Atkins ,  Stuart Benjamin Cook ,  Joaquin Vargas Calvet ,  Andrew Michael White ,  Karl Bailey ,  Corrine Jagneaux ,  Maika Lopati Mauga

IPC: B64C27/06 ,  B64C13/16 ,  B64C27/00 ,  B64C27/52 ,  B64C11/06 ,  B06B1/06 ,  B64C11/30 ,  B64C19/02

Abstract: The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.

公开(公告)号：US11027821B2

公开(公告)日：2021-06-08

申请号：US15876420

申请日：2018-01-22

Applicant: Bell Helicopter Textron Inc.

Inventor： Brady Garrett Atkins ,  Michael David Trantham ,  Paul David Ruckel

IPC: B64C13/16 ,  B64C29/00 ,  B64C13/50

Abstract: A system and method for preventing a maximum asymmetric condition between pylon tilt angles due to a degraded pylon in a fly-by-wire tiltrotor aircraft during transitions between airplane mode and helicopter mode includes a conversion system for imparting movement on a right and left pylon. A flight control computer is operatively connected to a set of transducers for measuring pylon angles. The flight control computer is further connected to a set of actuators which are attached to each pylon. The flight control computer receives flight dynamics input from the set of transducers and/or the pilot and sends pylon command to the set of actuators. The conversion system measures the difference between the pylon angles during the transition and provides a pylon command adjustment if the difference exceeds a preset threshold.

公开(公告)号：US20190257638A1

公开(公告)日：2019-08-22

申请号：US15902133

申请日：2018-02-22

Applicant: Bell Helicopter Textron Inc.

Inventor： David Bryan Roberts ,  Charles Eric Covington ,  Brady Garrett Atkins

IPC: G01B7/30 ,  G01B7/04 ,  G01B11/04 ,  G01B11/26 ,  G01D5/347

Abstract: A method and system to measure a parameter associated with a component, device, or system with a specified accuracy, including: providing one or more sensors operably disposed to detect the parameter; obtaining a coarse measurement of the parameter within a first range using the one or more sensors, wherein the first range includes minimum and maximum values for the parameter; obtaining a fine measurement of the parameter within a second range using the one or more sensors, wherein the second range is smaller than the first range and has a specified ratio to the first range that provides the specified accuracy; determining a current value of the parameter by combining the coarse and fine measurements; and providing the current value of the parameter to a communications interface, a storage device, a display, a control panel, a processor, a programmable logic controller, or an external device.

公开(公告)号：US20190241251A1

公开(公告)日：2019-08-08

申请号：US15887664

申请日：2018-02-02

Applicant: Bell Helicopter Textron Inc.

Inventor： Brady Garrett Atkins ,  Robert Paul Reynolds ,  Carlos Alexander Fenny ,  Charles Eric Covington

IPC: B64C11/38 ,  F01B25/10 ,  F01B9/00

CPC classification number: F16K31/047 ,  F16K11/20

Abstract: Systems and methods include providing an aircraft with a direct drive dual-concentric valve (D3V) having a body, an outer secondary spool coaxially located within a bore of the body and linearly displaceable relative to the body, an inner primary spool coaxially located within a bore of the secondary spool and linearly displaceable relative to the secondary spool and the body, and multiple motor assemblies coupled to the primary spool that provide selective displacement of the primary spool or the secondary spool. Each motor assembly includes a clutching mechanism that selectively couples a motor of the motor assembly to and from the primary spool.