公开(公告)号：US20220333567A1

公开(公告)日：2022-10-20

申请号：US17235225

申请日：2021-04-20

Applicant: Bell Textron Inc.

Inventor： Thomas PARSONS ,  Charles Eric COVINGTON

IPC: F02M35/10 ,  F02C3/00

Abstract: A method of optimizing engine air-mass-flow intake of an aircraft includes determining air mass flow (“M1”) at a forward-facing airframe inlet duct. The forward-facing airframe inlet duct includes an air-mass-flow bypass mechanism. The method also includes determining required air mass flow (“MR”) of an engine coupled to the forward-facing airframe inlet duct, determining an air-mass-flow difference (“M3”) between M1 and MR, and adjusting the air-mass-flow bypass mechanism to pass M3 such that at least a portion of M3 does not reach the engine.

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：US20220396353A1

公开(公告)日：2022-12-15

申请号：US17342963

申请日：2021-06-09

Applicant: Bell Textron Inc.

Inventor： Charles Eric COVINGTON ,  Chia-Wei SU ,  Darren Gregory LANG ,  Thomas PARSONS ,  Cody Earl FEGELY

IPC: B64C27/12 ,  B64D35/08

Abstract: A rotorcraft has a drive system including a main rotor coupled to a main rotor gearbox to rotate the main rotor at a rotor speed, a main engine coupled to the drive system to provide a first power, a supplemental engine coupled, when a first clutch is engaged, to the drive system to provide a second power additive to the first power, and a control system operable to control the main engine and the supplemental engine to provide a total power demand, where the main engine is controlled based on variations in rotor speed and a power compensation command to produce the first power, and the supplemental engine is controlled to produce the second power in response to a supplemental power demand.

公开(公告)号：US20220333562A1

公开(公告)日：2022-10-20

申请号：US17235239

申请日：2021-04-20

Applicant: Bell Textron Inc.

Inventor： Thomas PARSONS ,  Charles Eric COVINGTON

IPC: F02M35/10 ,  F02C3/00

Abstract: A system for optimizing engine air-mass-flow intake of an aircraft includes a forward-facing airframe-inlet duct interoperably coupled to an inlet of an engine of the aircraft, an air-mass-flow bypass mechanism coupled to the forward-facing airframe-inlet duct and adjustable to allow a selected amount of air entering an inlet of the forward-facing airframe-inlet duct to bypass the inlet of the engine, and an air-pressure sensor arranged in the forward-facing airframe-inlet duct adjacent to the inlet of the engine. A measured value (“PT1”) from the air-pressure sensor is used to determine a degree to which the air-mass-flow bypass mechanism is to be opened.

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.