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公开(公告)号：US20200241566A1
公开(公告)日：2020-07-30
申请号：US16257651
申请日：2019-01-25
Applicant: Bell Helicopter Textron Inc.
Inventor： Yann Lavallee , Eric Albert Sinusas , Robert Patrick Wardlaw
Abstract: A yaw control system for a rotorcraft featuring a floor mounted pair of pedals configured to measure an up and down motion of a pair of pedals and utilize that up and down motion as a yaw moment control input. The pair of pedals can rock laterally, fore and aft, or vertically. The pair of pedals can be mechanically interconnected to other pairs of pedals or electrically interconnected to duplicate motion across pairs of pedals.
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公开(公告)号：US10933980B2
公开(公告)日：2021-03-02
申请号：US16054027
申请日：2018-08-03
Applicant: Bell Helicopter Textron Inc.
Inventor： Eric Albert Sinusas , Edward Lambert , Yann Lavallee , Aaron Alexander Acee , Albert G. Brand
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.
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公开(公告)号：US20200290735A1
公开(公告)日：2020-09-17
申请号：US16354591
申请日：2019-03-15
Applicant: Bell Helicopter Textron Inc.
Inventor： Aaron Alexander Acee , Andrew Paul Haldeman , Eric Albert Sinusas , Yann Lavallee , Albert G. Brand
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.
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公开(公告)号：US20200055410A1
公开(公告)日：2020-02-20
申请号：US16103426
申请日：2018-08-14
Applicant: Bell Helicopter Textron Inc.
Inventor： Eric Albert Sinusas
Abstract: An exemplary method includes controlling a rotation rate of a rotor in a vehicle, detecting that an electric motor system is electrically energized and rotating the rotor at least at a minimum rotation rate that is greater than zero in response to the electric motor system being electrically energized. The rotor may be rotated at least at the minimum rotation rate when the electric motor system is energized and the motor is turned-off.
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公开(公告)号：US20190382109A1
公开(公告)日：2019-12-19
申请号：US16007666
申请日：2018-06-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Albert Gerard Brand , Eric Albert Sinusas
IPC: B64C27/82
Abstract: Systems and methods include providing a helicopter, with a fuselage, a tail boom extending from the fuselage, a main rotor system, and a tail rotor assembly disposed on an aft end of the tail boom. The tail rotor assembly includes a tail rotor housing, at least one normal ducted fan that generate anti-torque thrust to prevent rotation of the fuselage, and at least one canted ducted fan configured to generate both anti-torque thrust to prevent of the fuselage and lift to the tail boom in order to control the pitch of the helicopter. The canted ducted fans generate sufficient lift to prevent a nose-up orientation of the helicopter when the center of gravity of the helicopter is shifted rearward behind the main rotor system, while the normal ducted fans maintain sufficient anti-torque thrust to prevent rotation of the fuselage when the main rotor is operated.
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Patent Agency Ranking
公开(公告)号：US11427090B2
公开(公告)日：2022-08-30
申请号：US16103426
申请日：2018-08-14
Applicant: Bell Helicopter Textron Inc.
Inventor： Eric Albert Sinusas
Abstract: An exemplary method includes controlling a rotation rate of a rotor in a vehicle, detecting that an electric motor system is electrically energized and rotating the rotor at least at a minimum rotation rate that is greater than zero in response to the electric motor system being electrically energized. The rotor may be rotated at least at the minimum rotation rate when the electric motor system is energized and the motor is turned-off.
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公开(公告)号：US11148796B2
公开(公告)日：2021-10-19
申请号：US16007666
申请日：2018-06-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Albert Gerard Brand , Eric Albert Sinusas
IPC: B64C27/82
Abstract: Systems and methods include providing a helicopter, with a fuselage, a tail boom extending from the fuselage, a main rotor system, and a tail rotor assembly disposed on an aft end of the tail boom. The tail rotor assembly includes a tail rotor housing, at least one normal ducted fan that generate anti-torque thrust to prevent rotation of the fuselage, and at least one canted ducted fan configured to generate both anti-torque thrust to prevent of the fuselage and lift to the tail boom in order to control the pitch of the helicopter. The canted ducted fans generate sufficient lift to prevent a nose-up orientation of the helicopter when the center of gravity of the helicopter is shifted rearward behind the main rotor system, while the normal ducted fans maintain sufficient anti-torque thrust to prevent rotation of the fuselage when the main rotor is operated.
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公开(公告)号：US11281236B2
公开(公告)日：2022-03-22
申请号：US16257651
申请日：2019-01-25
Applicant: Bell Helicopter Textron Inc.
Inventor： Yann Lavallee , Eric Albert Sinusas , Robert Patrick Wardlaw
Abstract: A yaw control system for a rotorcraft featuring a floor mounted pair of pedals configured to measure an up and down motion of a pair of pedals and utilize that up and down motion as a yaw moment control input. The pair of pedals can rock laterally, fore and aft, or vertically. The pair of pedals can be mechanically interconnected to other pairs of pedals or electrically interconnected to duplicate motion across pairs of pedals.
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公开(公告)号：US11072422B2
公开(公告)日：2021-07-27
申请号：US16004375
申请日：2018-06-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Eric Albert Sinusas , Albert Gerard Brand
Abstract: Systems and methods include providing an aircraft with a fuselage, a tail boom or empennage extending from the fuselage, a main rotor, a tail rotor, and at least one counter torque device. The counter torque device provides counter torque to the fuselage to prevent rotation of fuselage when the main rotor is operated, particularly in right sideward flight (RSF) for conventional helicopters with a counter-clockwise rotating (when viewed from above the helicopter) main rotor.
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公开(公告)号：US20200156775A1
公开(公告)日：2020-05-21
申请号：US16196950
申请日：2018-11-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Eric Albert Sinusas , Thomas C. Parham, Jr. , Albert Gerard Brand
Abstract: A rotor system for a rotorcraft has a hub rotatable about an axis and a plurality of blades coupled to the hub for rotation therewith about the axis. Each blade is capable of rotation about a pitch axis relative to the hub, and a ring couples adjacent blades to each other.
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