公开(公告)号：US11340633B2

公开(公告)日：2022-05-24

申请号：US16555655

申请日：2019-08-29

Applicant: Bell Textron Inc.

Inventor： Derek William Heard ,  Richard Theodore Perryman ,  Nathan Craig Clark ,  Joshua Andrew Emrich ,  Yann Lavallee ,  Ralph Michael Gannarelli

IPC: B64C17/08 ,  G05D1/08

Abstract: A method of adjusting a center of gravity (CG) of an aircraft includes: inputting at least one load parameter into a flight computer, determining, via a processer of the flight computer, the CG of the aircraft. Responsive to a determination by the processor that the CG is outside of a CG envelope, moving at least a first movable ballast of a plurality of movable ballasts from a first ballast dock to a second ballast dock to move the CG toward the CG envelope. Each of the first and second ballast docks may include a housing and a first ballast tray secured within the housing and comprising a plurality of channels.

公开(公告)号：US20220411050A1

公开(公告)日：2022-12-29

申请号：US17357361

申请日：2021-06-24

Applicant: Bell Textron Inc.

Inventor： Yann Lavallee ,  Scott D. Poster

IPC: B64C27/56 ,  B64C27/82 ,  B64C27/06 ,  B64C27/12

Abstract: Tail rotor control system is described for helicopters. A pedal position sensor operable by a pilot yields greater tail rotor RPM relative to the main rotor RPM, giving the pilot increased control over the vehicle. This proves especially useful in certain situations, such as high altitude, where increasing tail rotor speed from main rotor speed can give a pilot increased maneuverability and stability.

公开(公告)号：US11414184B2

公开(公告)日：2022-08-16

申请号：US16354591

申请日：2019-03-15

Applicant: Bell Textron Inc.

Inventor： Aaron Alexander Acee ,  Andrew Paul Haldeman ,  Eric Albert Sinusas ,  Yann Lavallee ,  Albert G. Brand

IPC: B64C27/82 ,  B64D31/00 ,  H02P5/46

Abstract: An exemplary electric distributed propulsion system includes two or more rotors that are individually controlled by the rotational speed of associated motors, an input control connected to the associated motors to provide rotational speed control to the two or more rotors to produce a desired net thrust, and a logic connected to the input control and the associated motors, the logic for controlling speed and direction of the two or more rotors to achieve the desired net thrust and to avoid a motor speed condition.

公开(公告)号：US12202594B2

公开(公告)日：2025-01-21

申请号：US17165068

申请日：2021-02-02

Applicant: Bell Textron Inc.

Inventor： Eric Albert Sinusas ,  Edward Lambert ,  Yann Lavallee ,  Aaron Alexander Acee ,  Albert G. Brand

IPC: B64C19/02 ,  B64D31/06 ,  G01C23/00 ,  B64D45/00 ,  B64U10/17 ,  B64U30/20

Abstract: An aircraft having an electric motor coupled to a rotor and an instrument electronically connected to the electric motor and configured to communicate a time available value before a motor condition reaches a motor condition limit.

公开(公告)号：US11148786B2

公开(公告)日：2021-10-19

申请号：US16899295

申请日：2020-06-11

Applicant: Bell Textron Inc.

Inventor： Derek William Heard ,  Richard Theodore Perryman ,  Nathan Craig Clark ,  Joshua Andrew Emrich ,  Yann Lavallee ,  Ralph Michael Gannarelli

IPC: B64C17/00 ,  B64C17/08

Abstract: A movable ballast system for an aircraft includes first and second ballast docks secured to the aircraft. The first ballast dock includes a first housing and a first ballast tray and a first stop plate secured within the first housing. The first ballast tray includes a plurality of channels. The second ballast dock is positioned aft of a CG of the aircraft and includes a second housing and a second ballast tray and a second stop plate secured within the second housing. The second ballast tray includes a plurality of channels. The movable ballast system includes a plurality of movable ballasts, each movable ballast of the plurality of movable ballasts being configured to fit within at least one channel of each of the plurality of channels of the first and second ballast trays.

公开(公告)号：US11718392B2

公开(公告)日：2023-08-08

申请号：US17357361

申请日：2021-06-24

Applicant: Bell Textron Inc.

Inventor： Yann Lavallee ,  Scott D. Poster

IPC: B64C27/56 ,  B64C27/82 ,  B64C13/04 ,  B64C27/12

CPC classification number: B64C27/56 ,  B64C13/044 ,  B64C27/12 ,  B64C27/82

Abstract: Tail rotor control system is described for helicopters. A pedal position sensor operable by a pilot yields greater tail rotor RPM relative to the main rotor RPM, giving the pilot increased control over the vehicle. This proves especially useful in certain situations, such as high altitude, where increasing tail rotor speed from main rotor speed can give a pilot increased maneuverability and stability.

公开(公告)号：US11001373B2

公开(公告)日：2021-05-11

申请号：US16555515

申请日：2019-08-29

Applicant: Bell Textron Inc.

Inventor： Derek William Heard ,  Richard Theodore Perryman ,  Nathan Craig Clark ,  Joshua Andrew Emrich ,  Yann Lavallee ,  Ralph Michael Gannarelli

IPC: B64C17/00 ,  B64C27/04

Abstract: A movable ballast system for an aircraft includes first and second ballast docks secured to the aircraft. The first ballast dock includes a first housing and a first ballast tray secured within the first housing. The first ballast tray includes a plurality of channels. The second ballast dock is positioned aft of a CG of the aircraft and includes a second housing and a second ballast tray secured within the second housing. The second ballast tray includes a plurality of channels. The movable ballast system includes a plurality of movable ballasts, each movable ballast of the plurality of movable ballasts being configured to fit within at least one channel of each of the plurality of channels of the first and second ballast trays.