Patents by Inventor Frederick L. Bourne
Frederick L. Bourne 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: 11929617Abstract: A load control unit includes a first input terminal configured to receive power, a second input terminal configured to receive load information, a first output terminal configured to provide a first portion of the power to a first load, a second output terminal configured to provide a second portion of the power to a second load, a memory, and an electronic processor communicatively connected to the memory, first input terminal, the second input terminal, the first output terminal, and the second output terminal. The electronic processor is configured to measure the power received via the first input terminal, receive load parameters via the second input terminal, and dynamically control, in response to measuring the power and receiving the load parameters, at least one of the first load or the second load based on the power that is measured and the load parameters that are received.Type: GrantFiled: October 28, 2021Date of Patent: March 12, 2024Assignee: Lockheed Martin CorporationInventors: Christopher Patrick Sullivan, Melissa A. Baran, Matthew James Fogarty, Frederick L. Bourne
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Publication number: 20230139012Abstract: A load control unit includes a first input terminal configured to receive power, a second input terminal configured to receive load information, a first output terminal configured to provide a first portion of the power to a first load, a second output terminal configured to provide a second portion of the power to a second load, a memory, and an electronic processor communicatively connected to the memory, first input terminal, the second input terminal, the first output terminal, and the second output terminal. The electronic processor is configured to measure the power received via the first input terminal, receive load parameters via the second input terminal, and dynamically control, in response to measuring the power and receiving the load parameters, at least one of the first load or the second load based on the power that is measured and the load parameters that are received.Type: ApplicationFiled: October 28, 2021Publication date: May 4, 2023Inventors: Christopher Patrick Sullivan, Melissa A. Baran, Matthew James Fogarty, Frederick L. Bourne
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Patent number: 10745118Abstract: A rotary wing aircraft including a prime mover, a main rotor assembly having a first plurality of rotor blades operatively coupled to a main rotor shaft rotatable at a first speed ratio, a tail rotor assembly including a second plurality of rotor blades operatively coupled to a tail rotor shaft rotatable at a second speed ratio, and a variable ratio gearbox assembly mechanically connected to the tail rotor assembly. The variable ratio gearbox assembly operates to selectively vary the second speed ratio relative to the first speed ratio.Type: GrantFiled: August 17, 2017Date of Patent: August 18, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Frederick L. Bourne, Timothy F. Lauder, Nicholas D. Lappos
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Patent number: 10479511Abstract: A direct current (DC) deicing control system including a direct current (DC) power source, and a periodic deicing waveform generator electrically connected to the DC power source. The periodic deicing waveform generator outputs a switched DC voltage having a periodic electrical current waveform including periods of zero voltage and periods of non-zero voltage. The periods of zero voltage define arc extinguishing events reducing arc formation in the DC deicing control system.Type: GrantFiled: February 16, 2016Date of Patent: November 19, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Frederick L. Bourne, John Mihalakopoulos
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Patent number: 10392103Abstract: A detachable power transfer device for a rotary-wing aircraft includes a docking station integrated into the rotary-wing aircraft. A power pod of the detachable power transfer device is constructed and arranged to detachably connect to the docking station for transferring power to the rotary-wing aircraft.Type: GrantFiled: November 23, 2016Date of Patent: August 27, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Frederick L. Bourne, Peter James Waltner, Simon Gharibian
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Patent number: 10309304Abstract: One aspect is an electrical augmentation system for a gas turbine engine. The electrical augmentation system includes an electric motor operably coupled to a shaft of the gas turbine engine, and an energy storage device operable to provide a temporary increased current source to the electric motor. The electrical augmentation system includes a control system having a torque demand anticipation circuit operable to determine an anticipated torque increase condition for the gas turbine engine. Based on the anticipated torque increase condition, the torque demand anticipation circuit commands a temporary torque increase by the electric motor using the energy storage device.Type: GrantFiled: March 4, 2014Date of Patent: June 4, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Frederick L. Bourne, Mark Denton Bystry, Jr., Joseph Lawrence Simonetti
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Publication number: 20190089289Abstract: An electric motor includes a rotor assembly including a component rotatable about an axis and a stator assembly including a plurality of poles positioned adjacent the rotor assembly. Each of the plurality of poles is independently controllable to provide torque and speed control to the electric motor.Type: ApplicationFiled: September 21, 2017Publication date: March 21, 2019Inventors: Igor Cherepinsky, Frederick L. Bourne
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Patent number: 10087902Abstract: A method of operating an electrical system of an aircraft is provided. The method includes initiating a cross-start action for cross-starting a non-operative engine using a generator of an operative engine, entering a power limiting mode of a generator control unit (GCU) of the operative engine, remaining in the power limiting mode for a duration of the cross-start action and returning to the non-power limiting mode of the GCU of the operative engine upon completion of the cross-start action.Type: GrantFiled: May 11, 2016Date of Patent: October 2, 2018Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Mark P. Eisenhauer, Frederick L. Bourne, Matthew Fogarty
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Publication number: 20180093760Abstract: A flight control pump system includes an electrical machine configured to operate in a motor mode and in a generator mode. A pump is operatively connected to be driven by the electrical machine in the motor mode. An overriding clutch is operatively connected to the electrical machine and to the pump to transfer torque from a main transmission to drive the pump and the electrical machine in the generator mode, and to decouple the main transmission from the electrical machine and the pump in the motor mode.Type: ApplicationFiled: October 3, 2017Publication date: April 5, 2018Inventors: Scott J. Young, Frederick L. Bourne, William F. Lange
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Publication number: 20180086443Abstract: A rotary wing aircraft including a prime mover, a main rotor assembly having a first plurality of rotor blades operatively coupled to a main rotor shaft rotatable at a first speed ratio, a tail rotor assembly including a second plurality of rotor blades operatively coupled to a tail rotor shaft rotatable at a second speed ratio, and a variable ratio gearbox assembly mechanically connected to the tail rotor assembly. The variable ratio gearbox assembly operates to selectively vary the second speed ratio relative to the first speed ratio.Type: ApplicationFiled: August 17, 2017Publication date: March 29, 2018Inventors: Frederick L. Bourne, Timothy F. Lauder, Nicholas D. Lappos
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Patent number: 9909502Abstract: Embodiments are directed to an engine of an aircraft, a starter generator configured to receive power to cause the engine to start and to provide electrical power to at least one load, and a battery system comprising: a battery, and at least one of a controller and a regulator configured to limit an in-rush current to the battery following the starting of the engine.Type: GrantFiled: November 30, 2012Date of Patent: March 6, 2018Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Mark P. Eisenhauer, Frederick L. Bourne
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Patent number: 9849996Abstract: A method of engine electrical load shed control includes receiving an accessory load indicator corresponding to an accessory load of an engine. A request for acceleration of the engine is detected. One or more electrical buses are depowered based on the accessory load indicator exceeding a shedding threshold and detection of the request for acceleration of the engine.Type: GrantFiled: February 11, 2015Date of Patent: December 26, 2017Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: John H. Judge, Nicholas D. Kefalas, Mark P. Eisenhauer, Frederick L. Bourne, Robert J. Andrejczyk, Michael Patrick Wade
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Publication number: 20170174355Abstract: A helicopter includes a tail rotor, a primary drive system operatively connected to the tail rotor, and a secondary drive system operative connected to the tail rotor. The secondary drive system is configured to supplement torque provided to the tail rotor by the primary drive system. Related tail rotor drive systems and methods of applying torque to tail rotors are also described.Type: ApplicationFiled: November 18, 2016Publication date: June 22, 2017Inventors: Peter J. Waltner, Frederick L. Bourne, Joseph L. Simonetti, James R. Malo
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Publication number: 20170158354Abstract: A detachable power transfer device for a rotary-wing aircraft includes a docking station integrated into the rotary-wing aircraft. A power pod of the detachable power transfer device is constructed and arranged to detachably connect to the docking station for transferring power to the rotary-wing aircraft.Type: ApplicationFiled: November 23, 2016Publication date: June 8, 2017Inventors: Frederick L. Bourne, Peter James Waltner, Simon Gharibian
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Publication number: 20170089261Abstract: One aspect is an electrical augmentation system for a gas turbine engine. The electrical augmentation system includes an electric motor operably coupled to a shaft of the gas turbine engine, and an energy storage device operable to provide a temporary increased current source to the electric motor. The electrical augmentation system includes a control system having a torque demand anticipation circuit operable to determine an anticipated torque increase condition for the gas turbine engine. Based on the anticipated torque increase condition, the torque demand anticipation circuit commands a temporary torque increase by the electric motor using the energy storage device.Type: ApplicationFiled: March 4, 2014Publication date: March 30, 2017Inventors: Frederick L. Bourne, Mark Denton Bystry, Jr., Joseph Lawrence Simonetti
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Publication number: 20160332740Abstract: A method of operating an electrical system of an aircraft is provided. The method includes initiating a cross-start action for cross-starting a non-operative engine using a generator of an operative engine, entering a power limiting mode of a generator control unit (GCU) of the operative engine, remaining in the power limiting mode for a duration of the cross-start action and returning to the non-power limiting mode of the GCU of the operative engine upon completion of the cross-start action.Type: ApplicationFiled: May 11, 2016Publication date: November 17, 2016Inventors: Mark P. Eisenhauer, Frederick L. Bourne, Matthew Fogarty
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Publication number: 20160236787Abstract: A direct current (DC) deicing control system including a direct current (DC) power source, and a periodic deicing waveform generator electrically connected to the DC power source. The periodic deicing waveform generator outputs a switched DC voltage having a periodic electrical current waveform including periods of zero voltage and periods of non-zero voltage. The periods of zero voltage define arc extinguishing events reducing arc formation in the DC deicing control system.Type: ApplicationFiled: February 16, 2016Publication date: August 18, 2016Inventors: Frederick L. Bourne, John Mihalakopoulos
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Patent number: 9248909Abstract: A main rotor system of an aircraft is provided including a first rotor coupled to a transmission and configured to rotate about an axis in a first direction. A second rotor is similarly coupled to the transmission and is configured to rotate about the axis in a second direction. At least the first rotor includes an individual blade control system (IBCS) configured to adjust a pitch of each of a plurality of blade of the first rotor independently. A standpipe is fixedly attached to the aircraft. The standpipe is arranged such that the first rotor and the second rotor rotate relative to the standpipe. At least one slip ring is configured to transmit electrical power and/or a control signal to the at least one IBCS.Type: GrantFiled: July 23, 2013Date of Patent: February 2, 2016Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Erez Eller, Steven D. Weiner, Frederick L. Bourne
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Publication number: 20150225089Abstract: A method of engine electrical load shed control includes receiving an accessory load indicator corresponding to an accessory load of an engine. A request for acceleration of the engine is detected. One or more electrical buses are depowered based on the accessory load indicator exceeding a shedding threshold and detection of the request for acceleration of the engine.Type: ApplicationFiled: February 11, 2015Publication date: August 13, 2015Inventors: John H. Judge, Nicholas D. Kefalas, Mark P. Eisenhauer, Frederick L. Bourne, Robert J. Andrejczyk, Michael Patrick Wade
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Publication number: 20150028597Abstract: A main rotor system of an aircraft is provided including a first rotor coupled to a transmission and configured to rotate about an axis in a first direction. A second rotor is similarly coupled to the transmission and is configured to rotate about the axis in a second direction. At least the first rotor includes an individual blade control system (IBCS) configured to adjust a pitch of each of a plurality of blade of the first rotor independently. At least one slip ring is configured to transmit electrical power and/or a control signal to the at least one IBCS.Type: ApplicationFiled: July 23, 2013Publication date: January 29, 2015Applicant: Sikorsky Aircraft CorporationInventors: Erez Eller, Steven D. Weiner, Frederick L. Bourne