Patents by Inventor Eric Albert Sinusas
Eric Albert Sinusas has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11427090Abstract: 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.Type: GrantFiled: August 14, 2018Date of Patent: August 30, 2022Assignee: Textron Innovations Inc.Inventor: Eric Albert Sinusas
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Patent number: 11414184Abstract: 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.Type: GrantFiled: March 15, 2019Date of Patent: August 16, 2022Assignee: Textron Innovations Inc.Inventors: Aaron Alexander Acee, Andrew Paul Haldeman, Eric Albert Sinusas, Yann Lavallee, Albert G. Brand
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Patent number: 11281236Abstract: 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.Type: GrantFiled: January 25, 2019Date of Patent: March 22, 2022Assignee: Textron Innovations Inc.Inventors: Yann Lavallee, Eric Albert Sinusas, Robert Patrick Wardlaw
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Patent number: 11148796Abstract: 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.Type: GrantFiled: June 13, 2018Date of Patent: October 19, 2021Assignee: Textron Innovations Inc.Inventors: Albert Gerard Brand, Eric Albert Sinusas
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Publication number: 20210253225Abstract: 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.Type: ApplicationFiled: February 2, 2021Publication date: August 19, 2021Applicant: Bell Textron Inc.Inventors: Eric Albert SINUSAS, Edward LAMBERT, Yann LAVALLEE, Aaron Alexander ACEE, Albert G. BRAND
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Patent number: 11072422Abstract: 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.Type: GrantFiled: June 9, 2018Date of Patent: July 27, 2021Assignee: Textron Innovations Inc.Inventors: Eric Albert Sinusas, Albert Gerard Brand
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Patent number: 10933980Abstract: 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.Type: GrantFiled: August 3, 2018Date of Patent: March 2, 2021Assignee: Bell Helicopter Textron Inc.Inventors: Eric Albert Sinusas, Edward Lambert, Yann Lavallee, Aaron Alexander Acee, Albert G. Brand
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Patent number: 10906660Abstract: An exemplary vertical takeoff and landing includes a rotor driven by an electric motor, a generator located in a compartment and electrically connected to the electric motor, and an inlet formed through a side of the compartment to direct sideward airflow across the generator.Type: GrantFiled: August 9, 2018Date of Patent: February 2, 2021Assignee: Bell Textron Inc.Inventor: Eric Albert Sinusas
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Patent number: 10875636Abstract: 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.Type: GrantFiled: November 20, 2018Date of Patent: December 29, 2020Assignee: Textron Innovations Inc.Inventors: Eric Albert Sinusas, Thomas C. Parham, Jr., Albert Gerard Brand
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Publication number: 20200290735Abstract: 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.Type: ApplicationFiled: March 15, 2019Publication date: September 17, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Aaron Alexander Acee, Andrew Paul Haldeman, Eric Albert Sinusas, Yann Lavallee, Albert G. Brand
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Publication number: 20200283139Abstract: A hybrid rotor propulsion system includes a motor having a rotational output connected to a rotor and a prime mover connected to the motor through a rotational input, the prime mover configured to apply a rotational input speed to the motor.Type: ApplicationFiled: March 6, 2019Publication date: September 10, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Albert G. BRAND, Eric Albert SINUSAS
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Publication number: 20200241566Abstract: 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.Type: ApplicationFiled: January 25, 2019Publication date: July 30, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Yann Lavallee, Eric Albert Sinusas, Robert Patrick Wardlaw
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Publication number: 20200156775Abstract: 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.Type: ApplicationFiled: November 20, 2018Publication date: May 21, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Eric Albert Sinusas, Thomas C. Parham, Jr., Albert Gerard Brand
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Publication number: 20200055410Abstract: 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.Type: ApplicationFiled: August 14, 2018Publication date: February 20, 2020Applicant: Bell Helicpter Textron Inc.Inventor: Eric Albert Sinusas
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Publication number: 20200047898Abstract: An exemplary vertical takeoff and landing includes a rotor driven by an electric motor, a generator located in a compartment and electrically connected to the electric motor, and an inlet formed through a side of the compartment to direct sideward airflow across the generator.Type: ApplicationFiled: August 9, 2018Publication date: February 13, 2020Applicant: Bell Helicopter Textron Inc.Inventor: Eric Albert SINUSAS
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Publication number: 20200039639Abstract: 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.Type: ApplicationFiled: August 3, 2018Publication date: February 6, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Eric Albert SINUSAS, Edward LAMBERT, Yann LAVALLEE, Aaron Alexander ACEE, Albert G. BRAND
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Publication number: 20190382109Abstract: 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.Type: ApplicationFiled: June 13, 2018Publication date: December 19, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Albert Gerard Brand, Eric Albert Sinusas
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Publication number: 20190375498Abstract: 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.Type: ApplicationFiled: June 9, 2018Publication date: December 12, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Eric Albert Sinusas, Albert Gerard Brand