Patents by Inventor Erik Oltheten
Erik Oltheten 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: 11623736Abstract: An aircraft includes an electronically controlled engine (ECE) and a first and a second throttle control assembly. The first throttle control assembly includes a first throttle fly button configured to command a FLY mode and a first throttle idle button configured to command an IDLE mode. The second throttle control assembly includes a second throttle fly button configured to command the FLY mode and a second throttle idle button configured to command the IDLE mode.Type: GrantFiled: June 1, 2021Date of Patent: April 11, 2023Assignee: Textron Innovations Inc.Inventors: Erik Oltheten, Darren Gregory Lang, Charles Eric Covington
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Publication number: 20220033064Abstract: An aircraft includes an electronically controlled engine (ECE) and a first and a second throttle control assembly. The first throttle control assembly includes a first throttle fly button configured to command a FLY mode and a first throttle idle button configured to command an IDLE mode. The second throttle control assembly includes a second throttle fly button configured to command the FLY mode and a second throttle idle button configured to command the IDLE mode.Type: ApplicationFiled: June 1, 2021Publication date: February 3, 2022Applicant: Textron Innovations Inc.Inventors: Erik Oltheten, Darren Gregory Lang, Charles Eric Covington
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Patent number: 10145708Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.Type: GrantFiled: May 30, 2017Date of Patent: December 4, 2018Assignee: Textron Innovations Inc.Inventors: James M. McCollough, Erik Oltheten, Nicholas Lappos
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Publication number: 20170307401Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.Type: ApplicationFiled: May 30, 2017Publication date: October 26, 2017Applicant: TEXTRON INNOVATIONS INC.Inventors: James M. McCollough, Erik Oltheten, Nicholas Lappos
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Patent number: 9663243Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.Type: GrantFiled: May 31, 2016Date of Patent: May 30, 2017Assignee: Textron Innovations Inc.Inventors: James M. McCollough, Erik Oltheten, Nicholas Lappos
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Patent number: 9630724Abstract: According to one embodiment, a gauge display prioritization system comprises a priority engine and an output engine. The priority engine is operable to receive a measurement from a first sensor associated with a first aircraft component and a measurement from a second sensor associated with a second aircraft component, select a prioritization criterion based on the received measurements, and select one priority measurement from the received measurements based on the prioritization criterion. The output engine is operable to instruct a gauge disposed within a cockpit to display information representative of the one priority measurement to a pilot.Type: GrantFiled: July 1, 2013Date of Patent: April 25, 2017Assignee: Bell Helicopter Textron Inc.Inventors: Erik Oltheten, Aaron Halverson
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Publication number: 20160272342Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.Type: ApplicationFiled: May 31, 2016Publication date: September 22, 2016Applicant: TEXTRON INNOVATIONS INC.Inventors: James M. McCollough, Erik Oltheten, Nicholas Lappos
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Patent number: 9352849Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.Type: GrantFiled: May 18, 2015Date of Patent: May 31, 2016Assignee: Textron Innovations Inc.Inventors: James M. McCollough, Erik Oltheten, Nicholas Lappos
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Publication number: 20150321769Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.Type: ApplicationFiled: May 18, 2015Publication date: November 12, 2015Applicant: BELL HELICOPTER TEXTRON INC.Inventors: James M. McCollough, Erik Oltheten, Nicholas Lappos
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Patent number: 9096325Abstract: According to one embodiment, a method of managing pilot and copilot control of engine power in an aircraft includes receiving, from a first pilot input device, a first signal representative of a pilot selection of an increase power position or a decrease power position and receiving, from a second pilot input device, a second signal representative of a pilot selection of an increase power position or a decrease power position. One of the first signal and the second signal is prioritized. An aircraft engine is then instructed to change power output based on the prioritized signal.Type: GrantFiled: November 18, 2013Date of Patent: August 4, 2015Assignee: Bell Helicopter Textron Inc.Inventors: Erik Oltheten, James M. McCollough, Peter F. Scheidler, Jeffery S. Greenwood
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Publication number: 20150142215Abstract: According to one embodiment, a method of managing pilot and copilot control of engine power in an aircraft includes receiving, from a first pilot input device, a first signal representative of a pilot selection of an increase power position or a decrease power position and receiving, from a second pilot input device, a second signal representative of a pilot selection of an increase power position or a decrease power position. One of the first signal and the second signal is prioritized. An aircraft engine is then instructed to change power output based on the prioritized signal.Type: ApplicationFiled: November 18, 2013Publication date: May 21, 2015Applicant: Bell Helicopter Textron Inc.Inventors: Erik Oltheten, James M. McCollough, Peter F. Scheidler, Jeffrey S. Greenwood
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Patent number: 9035802Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.Type: GrantFiled: December 22, 2010Date of Patent: May 19, 2015Assignee: Textron Innovations Inc.Inventors: James M. McCollough, Erik Oltheten, Nicholas Lappos
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Publication number: 20140246537Abstract: According to one embodiment, a gauge display prioritization system comprises a priority engine and an output engine. The priority engine is operable to receive a measurement from a first sensor associated with a first aircraft component and a measurement from a second sensor associated with a second aircraft component, select a prioritization criterion based on the received measurements, and select one priority measurement from the received measurements based on the prioritization criterion. The output engine is operable to instruct a gauge disposed within a cockpit to display information representative of the one priority measurement to a pilot.Type: ApplicationFiled: July 1, 2013Publication date: September 4, 2014Inventors: Erik Oltheten, Aaron Halverson
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Publication number: 20130120165Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.Type: ApplicationFiled: December 22, 2010Publication date: May 16, 2013Applicant: Bell Helicopter Textron Inc.Inventors: James M. McCollough, Erik Oltheten, Nicholas Lappos
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Patent number: 7414544Abstract: A power situation indicator configured to provide power information in a rotorcraft is presented. The power situation indicator includes a detection unit configured to detect a current value of each of a plurality of control parameters, each of the plurality of control parameters including a pre-determined operating limit; a calculation unit configured to normalize on a common power scale (a) the current value and (b) the pre-determined operating limit of each of the plurality of control parameters, and a display unit configured to dynamically display on the common power scale a first moveable indicator and a second moveable indicator. The first moveable indicator is driven by one of the plurality of control parameters having the highest normalized current value and the second moveable indicator is driven by one of the plurality of control parameters having its normalized current value that is the closest to its corresponding normalized pre-determined operating limit.Type: GrantFiled: January 25, 2006Date of Patent: August 19, 2008Assignee: Bell Helicopter Textron, Inc.Inventors: Erik Oltheten, Jeffery Erwin
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Publication number: 20060287778Abstract: A power situation indicator configured to provide power information in a rotorcraft is presented. The power situation indicator includes a detection unit configured to detect a current value of each of a plurality of control parameters, each of the plurality of control parameters including a pre-determined operating limit; a calculation unit configured to normalize on a common power scale (a) the current value and (b) the pre-determined operating limit of each of the plurality of control parameters, and a display unit configured to dynamically display on the common power scale a first moveable indicator and a second moveable indicator. The first moveable indicator is driven by one of the plurality of control parameters having the highest normalized current value and the second moveable indicator is driven by one of the plurality of control parameters having its normalized current value that is the closest to its corresponding normalized pre-determined operating limit.Type: ApplicationFiled: January 25, 2006Publication date: December 21, 2006Applicant: Bell Helicopter Textron Inc.Inventors: Erik Oltheten, Jeffery Erwin