Patents by Inventor Albert G. Brand
Albert G. Brand 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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Publication number: 20240083581Abstract: Load management system and methods are described for aircraft, including tailsitters. A load management system can comprise a pole coupled the fuselage and free to rotate and swing. The pole can comprise a cargo hook and a distal end that can be releasably coupled to a cargo cable or cargo. The pole can be coupled near its distal end to a retractable cable that is deployed from a position aft of the pole. During landing, takeoff, and when otherwise in hover mode, the retractable cable can be retracted—holding the pole along or near the fuselage. During transition to, or during, flight mode, the retractable cable can be deployed which can harmonize the cargo's center of gravity with the needs of the tailsitter aircraft.Type: ApplicationFiled: September 12, 2022Publication date: March 14, 2024Inventors: Albert G. Brand, Robert P. Wardlaw
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Patent number: 11814162Abstract: One embodiment includes a rotary aircraft, including: a main drive rotor; an aircraft body mechanically coupled to the main drive rotor; and first and second flight assist wings passively rotatably coupled to the aircraft body.Type: GrantFiled: June 18, 2020Date of Patent: November 14, 2023Assignee: TEXTRON INNOVATIONS INC.Inventors: Albert G. Brand, Michael S. Seifert, Andrew Thomas Carter, Aaron Alexander Acee
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Patent number: 11801936Abstract: Embodiments are directed to a flight control system for a helicopter comprises a pilot interface configured to receive a control input, at least one electronically controlled actuator, and a computing device configured to translate the control input to an actuator command, wherein the computing device is further configured to apply yaw rate limits to the actuator command to avoid loss of tail rotor effectiveness. The yaw rate limits are associated with a vortex ring state (VRS) envelope for a tail rotor of the helicopter. The electronically controlled actuator comprises a tail rotor actuator. The control input is a pedal input.Type: GrantFiled: January 19, 2021Date of Patent: October 31, 2023Assignee: TEXTRON INNOVATIONS INC.Inventors: Albert G Brand, Bradley P. Regnier, Matthew J. Hill
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Publication number: 20230278701Abstract: A landing wheel assembly for a rotorcraft having a light on gear phase during takeoff and landing includes a tire and an anti-roll oscillation rim. The tire has first and second side walls and forms a center aperture. The anti-roll oscillation rim includes a center disc disposed in the aperture of the tire, a first side wall support plate protruding from the center disc and extending at least 25 percent of the vertical length of the first side wall of the tire and a second side wall support plate protruding from the center disc and extending at least 25 percent of the vertical length of the second side wall of the tire. The first and second side wall support plates support the first and second side walls, respectively, to stiffen the tire in the light on gear phase of takeoff and landing, thereby reducing roll oscillations of the rotorcraft.Type: ApplicationFiled: March 5, 2022Publication date: September 7, 2023Applicant: Textron Innovations Inc.Inventors: Albert G. Brand, Michael Pujol, Casey T. Johnson, Marko Vuga
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Patent number: 11433997Abstract: A method of providing an anti-torque force in a rotorcraft with an anti-torque system comprised of a primary ducted tail rotor system mechanically connected to an engine, and a secondary ducted tail rotor system electrically connected to an electric power supply. The method includes receiving an indication of a change in the operating condition of the anti-torque system based upon a change in a rotorcraft condition input, a feedback input associated with a primary ducted tail rotor system and/or a secondary ducted tail rotor system, and/or a pilot input; responsive to the indication of the change, determining, by a control system, an anti-torque control input including at least a secondary output command for controlling the secondary ducted tail rotor system; and transmitting the secondary output command to the secondary ducted tail rotor system to energize at least one ducted tail rotor assembly therein to provide the second anti-torque force.Type: GrantFiled: April 30, 2019Date of Patent: September 6, 2022Assignee: Textron Innovations Inc.Inventors: Aaron A. Acee, Albert G. Brand, Frank B. Stamps
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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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Publication number: 20220227488Abstract: Embodiments are directed to a flight control system for a helicopter comprises a pilot interface configured to receive a control input, at least one electronically controlled actuator, and a computing device configured to translate the control input to an actuator command, wherein the computing device is further configured to apply yaw rate limits to the actuator command to avoid loss of tail rotor effectiveness. The yaw rate limits are associated with a vortex ring state (VRS) envelope for a tail rotor of the helicopter. The electronically controlled actuator comprises a tail rotor actuator. The control input is a pedal input.Type: ApplicationFiled: January 19, 2021Publication date: July 21, 2022Applicant: TEXTRON INNOVATIONS INC.Inventors: Albert G. Brand, Bradley P. Regnier, Matthew J. Hill
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Patent number: 11273911Abstract: An electric power tethering system for an aircraft having a vertical takeoff and landing flight mode including a takeoff phase and/or a hover phase includes a surface power source and a power tether having a surface end configured to couple to the surface power source and an aircraft end configured to couple to the aircraft. The power tether is configured to transmit power from the surface power source to the aircraft in the takeoff phase and/or the hover phase. The power tether is detachable to decouple the surface power source from the aircraft in response to a power tether release event during flight.Type: GrantFiled: August 20, 2019Date of Patent: March 15, 2022Assignee: Textron Innovations Inc.Inventors: Albert G. Brand, Scott David Poster
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Publication number: 20210394894Abstract: One embodiment includes a rotary aircraft, including: a main drive rotor; an aircraft body mechanically coupled to the main drive rotor; and first and second flight assist wings passively rotatably coupled to the aircraft body.Type: ApplicationFiled: June 18, 2020Publication date: December 23, 2021Inventors: Albert G. Brand, Michael S. Seifert, Andrew Thomas Carter, Aaron Alexander Acee
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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: 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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Publication number: 20210053676Abstract: An electric power tethering system for an aircraft having a vertical takeoff and landing flight mode including a takeoff phase and/or a hover phase includes a surface power source and a power tether having a surface end configured to couple to the surface power source and an aircraft end configured to couple to the aircraft. The power tether is configured to transmit power from the surface power source to the aircraft in the takeoff phase and/or the hover phase. The power tether is detachable to decouple the surface power source from the aircraft in response to a power tether release event during flight.Type: ApplicationFiled: August 20, 2019Publication date: February 25, 2021Applicant: Bell Textron Inc.Inventors: Albert G. Brand, Scott David Poster
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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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Patent number: 10752352Abstract: A dual rotor propulsion system for a tiltrotor aircraft having VTOL and forward flight modes. The dual rotor propulsion system includes an engine operable to provide an input torque to a transmission that, responsive thereto, generates an output torque. A first output shaft is coupled to the transmission and is operable to receive a first portion of the output torque. A first rotor assembly is coupled to and rotatable with the first output shaft. A second output shaft is coupled to the transmission and is operable to receive a second portion of the output torque. A second rotor assembly is coupled to and rotatable with the second output shaft. In operation, the first and second rotor assemblies rotate coaxially, the first rotor assembly is a different diameter than the second rotor assembly and the first rotor assembly is stoppable and foldable in the forward flight mode.Type: GrantFiled: December 7, 2017Date of Patent: August 25, 2020Assignee: Textron Innovations Inc.Inventors: Albert G. Brand, Mark Loring Isaac, Frank Bradley Stamps, Russell Lee Mueller
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Patent number: 10633086Abstract: A rotorcraft comprises a fuselage, a tail boom, a rotor system, and a centrifugal blower system. The centrifugal blower system comprises a centrifugal blower configured to generate thrust using an airflow, wherein the centrifugal blower is located within the tail boom. The centrifugal blower system also comprises a plurality of ducts configured to control the thrust generated by the centrifugal blower, wherein the plurality of ducts is located on a portion of the tail boom surrounding the centrifugal blower, and wherein the plurality of ducts comprises one or more adjustable ducts configured to vary a size of an associated duct opening.Type: GrantFiled: March 23, 2017Date of Patent: April 28, 2020Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Matthew R. Carr, Matthew E. Louis, Kirk L. Groninga, Daniel B. Robertson, Frank B. Stamps, Albert G. Brand, Eric A. 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: 20200023958Abstract: A method of providing an anti-torque force in a rotorcraft with an anti-torque system comprised of a primary ducted tail rotor system mechanically connected to an engine, and a secondary ducted tail rotor system electrically connected to an electric power supply. The method includes receiving an indication of a change in the operating condition of the anti-torque system based upon a change in a rotorcraft condition input, a feedback input associated with a primary ducted tail rotor system and/or a secondary ducted tail rotor system, and/or a pilot input; responsive to the indication of the change, determining, by a control system, an anti-torque control input including at least a secondary output command for controlling the secondary ducted tail rotor system; and transmitting the secondary output command to the secondary ducted tail rotor system to energize at least one ducted tail rotor assembly therein to provide the second anti-torque force.Type: ApplicationFiled: April 30, 2019Publication date: January 23, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Aaron A. Acee, Albert G. Brand, Frank B. Stamps
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Publication number: 20190176980Abstract: A dual rotor propulsion system for a tiltrotor aircraft having VTOL and forward flight modes. The dual rotor propulsion system includes an engine operable to provide an input torque to a transmission that, responsive thereto, generates an output torque. A first output shaft is coupled to the transmission and is operable to receive a first portion of the output torque. A first rotor assembly is coupled to and rotatable with the first output shaft. A second output shaft is coupled to the transmission and is operable to receive a second portion of the output torque. A second rotor assembly is coupled to and rotatable with the second output shaft. In operation, the first and second rotor assemblies rotate coaxially, the first rotor assembly is a different diameter than the second rotor assembly and the first rotor assembly is stoppable and foldable in the forward flight mode.Type: ApplicationFiled: December 7, 2017Publication date: June 13, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Albert G. Brand, Mark Loring Isaac, Frank Bradley Stamps, Russell Lee Mueller
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Patent number: 10196151Abstract: A rotorcraft includes a fuselage having a fuel tank receiving assembly with a fuel tank positioned therein. The fuel tank including a plurality of interconnected fuel bags operable to contain liquid fuel. A network of straps is disposed about the fuel tank forming a restraint assembly. The network of straps includes at least one perimeter strap extending at least partially about at least two fuel bags and at least one surrounding strap extending at least partially about the at least two fuel bags. The at least one perimeter strap has at least two intersections with the at least one surrounding strap.Type: GrantFiled: May 2, 2016Date of Patent: February 5, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Martin Peryea, Michael Reaugh Smith, Douglas Hamelwright, Jr., Albert G. Brand, Nicholas J. Plagianos, Joshua Emrich, Timothy Carr