公开(公告)号：US20220219810A1

公开(公告)日：2022-07-14

申请号：US17145920

申请日：2021-01-11

Applicant: Bell Textron Inc.

Inventor： Clifton L. HARRELL ,  Charles Eric COVINGTON ,  David A. ADJEI ,  Kevin Matthew TRENDEL ,  Michael David TRANTHAM ,  Randall JOHNSON

IPC: B64C19/02 ,  G05D1/10

Abstract: In an embodiment, an aircraft includes a pilot input device, a position sensor coupled to the pilot input device, a flight condition sensor and a flight control computer (FCC). The FCC includes a first microprocessor and a second microprocessor. The first microprocessor is configured to receive input data from the position sensor and the condition sensor and determine therefrom a first output. The second microprocessor is configured to receive input data from the position sensor and the condition sensor and determine therefrom a second output. The FCC is configured to compare the first output and the second output to yield resultant data. Responsive to a determination that the first output and the second output do not match, the FCC is configured to execute first remediation logic if the resultant data satisfies first error criteria and to execute second remediation logic if the resultant data satisfies second error criteria.

公开(公告)号：US20210403147A1

公开(公告)日：2021-12-30

申请号：US16915877

申请日：2020-06-29

Applicant: Bell Textron Inc.

Inventor： Charles Eric COVINGTON ,  Randall Lee JOHNSON ,  Hunter Barton NELSON ,  Michael David TRANTHAM

IPC: B64C27/00 ,  B64C27/57

Abstract: A rotorcraft comprising a rotor blade designed to flap about a hinge point, a measurement system designed to measure blade flapping, and a processing system designed to alter blade flapping measurements. The processing system further comprises a correction process to alter a blade flapping measurement dependent on rotor RPM or rotor torque.

公开(公告)号：US20200292410A1

公开(公告)日：2020-09-17

申请号：US16678009

申请日：2019-11-08

Applicant: Bell Textron Inc.

Inventor： Charles Eric COVINGTON ,  Michael David TRANTHAM ,  Evan Butler BENNETT

IPC: G01M5/00 ,  B64C27/00 ,  B64C27/02 ,  B64C27/51

Abstract: An example of a rotor-state determining method for a rotor system includes, by a flight control computer, collecting data from a first sensor positioned on a first component of the rotorcraft, wherein the first sensor is isolated from movement of a rotor blade, collecting data from a second sensor positioned on a second component of the rotor system, wherein the second sensor detects movement of the rotor blade, filtering the data collected by the first sensor to remove noise from the data collected by the first sensor, filtering the data collected by the second sensor to remove noise from the data collected by the second sensor, calculating a difference between the filtered first data and the filtered second data to determine a parameter of the rotor blade, and responsive to the motion of the rotor blade, taking a corrective action.

公开(公告)号：US20210261237A1

公开(公告)日：2021-08-26

申请号：US17317657

申请日：2021-05-11

Applicant: Bell 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.