Patents by Inventor Kevin L. Bredenbeck
Kevin L. Bredenbeck 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: 11194349Abstract: A method of automating entry of an aircraft into autorotation includes detecting a loss of engine power, analyzing a sensed height and sensed airspeed of the aircraft, determining an adjusted position of one or more control surfaces of the aircraft in response to the sensed height and sensed airspeed, and automatically moving the one or more control surfaces to the adjusted position.Type: GrantFiled: June 21, 2017Date of Patent: December 7, 2021Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Matthew A. White, Matthew T. Luszcz, Kevin L. Bredenbeck, William C. Fell, Jr.
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Patent number: 11040770Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A cockpit in the airframe, the cockpit including two seats and a single collective control input positioned between the two seats.Type: GrantFiled: September 30, 2015Date of Patent: June 22, 2021Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Kevin L. Bredenbeck, William Fell, Erez Eller
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Patent number: 11021241Abstract: An aircraft is provided and includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe, at least one sensor and at least one inertial measurement unit (IMU) to sense current flight conditions of the aircraft, an interface to execute controls of a main rotor assembly in accordance with control commands and at least one flight control computer (FCC) to issue the control commands. The at least one FCC includes a central processing unit (CPU) and a memory having logic and executable instructions stored thereon, which, when executed, cause the CPU to issue the control commands based on the current flight conditions and a result of an execution of the logic for the current flight conditions.Type: GrantFiled: September 29, 2015Date of Patent: June 1, 2021Assignee: Sikorsky Aircraft CorporationInventors: Kevin L. Bredenbeck, Bryan S. Cotton, Kenneth C. Arifian, Erez Eller, Matthew T. Luszcz
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Patent number: 10676185Abstract: A pitch control system configured to vary a pitch angle of at least one of a plurality of propeller blades of a propeller system is provided including a switch movable between a neutral position and a plurality of non-neutral positions. Movement of the switch to a first non-neutral position generates a command to move the propeller blades in a first direction. Movement of the switch to a second non-neutral position generates a command to move the propeller blades in a second direction. Movement of the switch to a third non-neutral position generates a command to move the propeller blades to a zero thrust position.Type: GrantFiled: August 27, 2015Date of Patent: June 9, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Kevin L. Bredenbeck, Jr., Bryan S. Cotton, Mark K. Wilson
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Patent number: 10647422Abstract: A pitch control system configured to vary a pitch angle of at least one of a plurality of propeller blades of a propeller system is provided including a switch movable between a neutral position and a plurality of non-neutral positions. Movement of the switch to a first non-neutral position generates a command to move the propeller blades in a first direction. Movement of the switch to a second non-neutral position generates a command to move the propeller blades in a second direction. Movement of the switch to a third non-neutral position generates a command to move the propeller blades to a zero thrust position.Type: GrantFiled: May 13, 2019Date of Patent: May 12, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Kevin L. Bredenbeck, Bryan S. Cotton, Mark K. Wilson
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Patent number: 10619698Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly composed of a plurality of blades and a lower rotor assembly composed of a plurality of blades. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A flight control system to control the upper rotor assembly and the lower rotor assembly, wherein the flight control system is configured to control lift offset of the upper rotor assembly and the lower rotor assembly.Type: GrantFiled: September 30, 2015Date of Patent: April 14, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Erez Eller, Matthew T. Luszcz, Kenneth C. Arifian, Kevin L. Bredenbeck, Bryan S. Cotton
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Patent number: 10618635Abstract: A fly-by-wire aircraft and method of flying a fly-by-wire aircraft is disclosed. The aircraft includes a control system for flying the aircraft in one of a proportional ground control mode and a model following controls mode. A control device at a control interface of the aircraft selectively activates a trim follow up function in the control system. When flying the aircraft in a proportional ground control mode, trim follow up function can be activated. The control system can then transition into the model following controls mode with the trim follow up function activated to reduce transient behavior.Type: GrantFiled: January 12, 2017Date of Patent: April 14, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Leonard M. Wengler, III, Kevin L. Bredenbeck, Matthew T. Luszcz, Matthew A. White, William Fell
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Publication number: 20200023956Abstract: A pitch control system configured to vary a pitch angle of at least one of a plurality of propeller blades of a propeller system is provided including a switch movable between a neutral position and a plurality of non-neutral positions. Movement of the switch to a first non-neutral position generates a command to move the propeller blades in a first direction. Movement of the switch to a second non-neutral position generates a command to move the propeller blades in a second direction. Movement of the switch to a third non-neutral position generates a command to move the propeller blades to a zero thrust position.Type: ApplicationFiled: May 13, 2019Publication date: January 23, 2020Inventors: Kevin L. Bredenbeck, Bryan S. Cotton, Mark K. Wilson
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Patent number: 10443674Abstract: A method of controlling noise of an aircraft includes storing a plurality of predefined noise modes; receiving a selection of a selected noise mode from the plurality of predefined noise modes, the selected noise mode identifying at least one operational parameter; and controlling the aircraft in response to the at least one operational parameter.Type: GrantFiled: July 27, 2015Date of Patent: October 15, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Erez Eller, William J. Eadie, Kevin L. Bredenbeck, Steven D. Weiner
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Publication number: 20170369160Abstract: A method of automating entry of an aircraft into autorotation includes detecting a loss of engine power, analyzing a sensed height and sensed airspeed of the aircraft, determining an adjusted position of one or more control surfaces of the aircraft in response to the sensed height and sensed airspeed, and automatically moving the one or more control surfaces to the adjusted position.Type: ApplicationFiled: June 21, 2017Publication date: December 28, 2017Inventors: Matthew A. White, Matthew T. Luszcz, Kevin L. Bredenbeck, William C. Fell, JR.
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Publication number: 20170305534Abstract: An aircraft includes an airframe having an extending tail, a counter rotating, coaxial main rotor assembly disposed at the airframe including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the extending tail and providing translational thrust to the airframe. A fly by wire control system for the aircraft includes a flight control system configured to receive a plurality of inputs and a flight control computer to translate the inputs into commands and issue the commands to one or more controlled elements of the aircraft. A fly by wire control system for a dual coaxial rotor rotorcraft with auxiliary propulsor includes a flight control system configured to receive a plurality of inputs and a flight control computer to translate the inputs into commands and issue the commands to one or more controlled elements of the rotorcraft.Type: ApplicationFiled: September 28, 2015Publication date: October 26, 2017Inventors: Kevin L. Bredenbeck, Steven D. Weiner, David M. Walsh, Bryan S. Cotton, Kenneth C. Arifian
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Publication number: 20170305540Abstract: A method of controlling noise of an aircraft includes storing a plurality of predefined noise modes; receiving a selection of a selected noise mode from the plurality of predefined noise modes, the selected noise mode identifying at least one operational parameter; and controlling the aircraft in response to the at least one operational parameter.Type: ApplicationFiled: July 27, 2015Publication date: October 26, 2017Inventors: Erez Eller, William J. Eadie, Kevin L. Bredenbeck, Steven D. Weiner
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Publication number: 20170277201Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. The main rotor assembly and the translational thrust system are configured to provide hover nose down, hover nose up and hover level modes of flight.Type: ApplicationFiled: September 24, 2015Publication date: September 28, 2017Inventors: Kevin L. BREDENBECK, Steven D. WEINER, Erez ELLER, Matthew T. LUSZCZ
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Publication number: 20170274987Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A cockpit in the airframe, the cockpit including two seats and a single collective control input positioned between the two seats.Type: ApplicationFiled: September 30, 2015Publication date: September 28, 2017Inventors: Kevin L. BREDENBECK, William FELL, Erez ELLER
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Publication number: 20170233068Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly composed of a plurality of blades and a lower rotor assembly composed of a plurality of blades. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A flight control system to control the upper rotor assembly and the lower rotor assembly, wherein the flight control system is configured to control lift offset of the upper rotor assembly and the lower rotor assembly.Type: ApplicationFiled: September 30, 2015Publication date: August 17, 2017Inventors: Erez Eller, Matthew T. Luszcz, Kenneth C. Arifian, Kevin L. Bredenbeck, Bryan S. Cotton
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Publication number: 20170233066Abstract: A pitch control system configured to vary a pitch angle of at least one of a plurality of propeller blades of a propeller system is provided including a switch movable between a neutral position and a plurality of non-neutral positions. Movement of the switch to a first non-neutral position generates a command to move the propeller blades in a first direction. Movement of the switch to a second non-neutral position generates a command to move the propeller blades in a second direction. Movement of the switch to a third non-neutral position generates a command to move the propeller blades to a zero thrust position.Type: ApplicationFiled: August 27, 2015Publication date: August 17, 2017Inventors: Kevin L. Bredenbeck, JR., Bryan S. Cotton, Mark K. Wilson
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Publication number: 20170225797Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. The upper rotor assembly and the lower rotor assembly each include a plurality of blades. A translational thrust system is positioned at the extending tail and provides translational thrust to the airframe. The plurality of blades of the main rotor assembly extend beyond a nose of the aircraft by about 13 inches.Type: ApplicationFiled: July 1, 2015Publication date: August 10, 2017Inventors: Kevin L. Bredenbeck, William Fell, Steven D. Weiner
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Publication number: 20170220048Abstract: A method of controlling a rotary wing aircraft includes accelerating the aircraft in a fore direction independently of cyclic control of the main rotor and pitch of the aircraft.Type: ApplicationFiled: September 25, 2015Publication date: August 3, 2017Inventors: William J. Eadie, Steven D. Weiner, Kevin L. Bredenbeck
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Publication number: 20170217582Abstract: An aircraft is provided and includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe, at least one sensor and at least one inertial measurement unit (IMU) to sense current flight conditions of the aircraft, an interface to execute controls of a main rotor assembly in accordance with control commands and at least one flight control computer (FCC) to issue the control commands. The at least one FCC includes a central processing unit (CPU) and a memory having logic and executable instructions stored thereon, which, when executed, cause the CPU to issue the control commands based on the current flight conditions and a result of an execution of the logic for the current flight conditions.Type: ApplicationFiled: September 29, 2015Publication date: August 3, 2017Inventors: Kevin L. BREDENBECK, Bryan S. COTTON, Kenneth C. ARIFIAN, Erez ELLER, Matthew T. LUSZCZ
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Publication number: 20170197705Abstract: A fly-by-wire aircraft and method of flying a fly-by-wire aircraft is disclosed. The aircraft includes a control system for flying the aircraft in one of a proportional ground control mode and a model following controls mode. A control device at a control interface of the aircraft selectively activates a trim follow up function in the control system. When flying the aircraft in a proportional ground control mode, trim follow up function can be activated. The control system can then transition into the model following controls mode with the trim follow up function activated to reduce transient behavior.Type: ApplicationFiled: January 12, 2017Publication date: July 13, 2017Inventors: Leonard M. Wengler, III, Kevin L. Bredenbeck, Matthew T. Luszcz, Matthew A. White, William Fell