Patents by Inventor Jukka Matti Hirvonen
Jukka Matti Hirvonen 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: 20210233413Abstract: A method for determining a Mach cutoff flight profile for an aircraft comprises receiving a flight origination and destination; receiving an initial atmospheric profile forecast; receiving user preferences on flight parameters to be optimized; computing a user cost function; determining a flight profile which implements Mach cutoff; receiving updates on the atmospheric profile forecast; determining potential sonic boom incidents; determining one or more sonic boom avoidance modifications to the flight profile that will avoid sonic boom incidents and not exceed the user cost function if potential sonic boom incidents are determined; presenting one or more sonic boom avoidance modifications to a pilot of the aircraft if potential sonic boom incidents are determined; receiving selection of one of the sonic boom avoidance modifications if potential sonic boom incidents are determined; and updating the flight profile with the selected sonic boom avoidance modification if potential sonic boom incidents are determinType: ApplicationFiled: January 23, 2020Publication date: July 29, 2021Applicant: Aerion Intellectual Property Management CorporationInventors: Harold Eugene Holloway, Jason Rahe Matisheck, Laurens Jozef A Voet, German Andres Garzon, Andrew Joseph Hellen, Jukka Matti Hirvonen, Andrew Donald Meeker
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Patent number: 10745141Abstract: A rudder bias system for an aircraft with a right engine and a left engine includes a component determining a left and right primary and secondary thrust estimates. The system includes a left engine thrust estimate selector determining a left selected estimate based on the left thrust estimates and a right engine thrust estimate selector determining a right selected estimate based on the right thrust estimates. The system includes an enable and mode component determining one or more corresponding validities for the thrust estimates. The system includes a control component generating an engage command based on a thrust differential between the right engine and the left engine, calculated from the left selected estimate and the right selected estimate and a torque command based on an equivalent pedal force assistance calculated as a difference between the thrust differential and an activation threshold.Type: GrantFiled: December 1, 2016Date of Patent: August 18, 2020Assignee: HONDA PATENTS & TECHNOLOGIES NORTH AMERICA, LLCInventors: Jukka Matti Hirvonen, Nilesh Arun Sahani, Jeremy Nathaniel Montgomery
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Patent number: 10723473Abstract: According to one or more aspects, a control system for managing operational limits associated with two or more actuators includes a controller. The controller may continually monitor a first operational limit associated with a first actuator and a first operational limit associated with a second actuator. The controller may determine a first overall distributed control system operating limit based on the first operational limit associated with the first actuator, the first operational limit associated with the second actuator, and a type of operational limit associated with both operational limits.Type: GrantFiled: December 1, 2016Date of Patent: July 28, 2020Assignee: HONDA PATENTS & TECHNOLOGIES NORTH AMERICA, LLCInventor: Jukka Matti Hirvonen
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Publication number: 20190009922Abstract: A rudder bias system for an aircraft with a right engine and a left engine includes a component determining a left and right primary and secondary thrust estimates. The system includes a left engine thrust estimate selector determining a left selected estimate based on the left thrust estimates and a right engine thrust estimate selector determining a right selected estimate based on the right thrust estimates. The system includes an enable and mode component determining one or more corresponding validities for the thrust estimates. The system includes a control component generating an engage command based on a thrust differential between the right engine and the left engine, calculated from the left selected estimate and the right selected estimate and a torque command based on an equivalent pedal force assistance calculated as a difference between the thrust differential and an activation threshold.Type: ApplicationFiled: December 1, 2016Publication date: January 10, 2019Inventors: Jukka Matti Hirvonen, Nilesh Arun Sahani, Jeremy Nathaniel Montgomery
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Publication number: 20180362176Abstract: According to one or more aspects, a control system for managing operational limits associated with two or more actuators includes a controller. The controller may continually monitor a first operational limit associated with a first actuator and a first operational limit associated with a second actuator. The controller may determine a first overall distributed control system operating limit based on the first operational limit associated with the first actuator, the first operational limit associated with the second actuator, and a type of operational limit associated with both operational limits.Type: ApplicationFiled: December 1, 2016Publication date: December 20, 2018Inventor: Jukka Matti Hirvonen
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Patent number: 8235328Abstract: Embodiments of the invention relate to a flight control system for controlling an aircraft during flight. The flight control system may include a primary controller configured to receive an input from a pilot and to output a primary control signal and a primary transmission path connected to the primary controller and configured to relay the primary control signal. The flight control system may also include a backup controller configured to receive the input from the pilot and to output a backup control signal and a backup transmission path connected to the backup controller and configured to relay the backup control signal. Additionally, the flight control system may include an actuator having a remote electronics unit configured to receive the primary control signal and the backup control signal and to determine if the primary control signal is available and valid.Type: GrantFiled: June 23, 2011Date of Patent: August 7, 2012Assignee: Gulfstream Aerospace CorporationInventor: Jukka Matti Hirvonen
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Patent number: 8104720Abstract: Embodiments of the invention relate to a flight control system for controlling an aircraft in flight having a backup control system integrated into an active control stick. The actuated control stick may include a processing unit that includes independent and separate hardware and/or software dedicated to the primary control system and the backup control system. For the primary control system, the processing unit may receive a sensed primary control stick signal and communicate with a primary processor, which may be configured to generate a primary control signal. For the backup control system, the processing unit may receive a sensed backup control stick signal and generate a backup control signal. The processing unit may also generate tactile signal for use by the actuated control stick to adjust the feel of a pilot's control stick.Type: GrantFiled: February 1, 2011Date of Patent: January 31, 2012Assignee: Gulfstream Aerospace CorporationInventors: Jukka Matti Hirvonen, Gary Palfreyman
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Publication number: 20110248121Abstract: Embodiments of the invention relate to a flight control system for controlling an aircraft during flight. The flight control system may include a primary controller configured to receive an input from a pilot and to output a primary control signal and a primary transmission path connected to the primary controller and configured to relay the primary control signal. The flight control system may also include a backup controller configured to receive the input from the pilot and to output a backup control signal and a backup transmission path connected to the backup controller and configured to relay the backup control signal. Additionally, the flight control system may include an actuator having a remote electronics unit configured to receive the primary control signal and the backup control signal and to determine if the primary control signal is available and valid.Type: ApplicationFiled: June 23, 2011Publication date: October 13, 2011Inventor: Jukka Matti Hirvonen
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Publication number: 20110190965Abstract: Embodiments of the invention relate to a flight control system for controlling an aircraft in flight having a backup control system integrated into an active control stick. The actuated control stick may include a processing unit that includes independent and separate hardware and/or software dedicated to the primary control system and the backup control system. For the primary control system, the processing unit may receive a sensed primary control stick signal and communicate with a primary processor, which may be configured to generate a primary control signal. For the backup control system, the processing unit may receive a sensed backup control stick signal and generate a backup control signal. The processing unit may also generate tactile signal for use by the actuated control stick to adjust the feel of a pilot's control stick.Type: ApplicationFiled: February 1, 2011Publication date: August 4, 2011Applicant: Gulfstream Aerospace CorporationInventors: Jukka Matti Hirvonen, Gary Palfreyman
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Patent number: 7984878Abstract: Embodiments of the invention relate to a flight control system for controlling an aircraft during flight. The flight control system may include a primary controller configured to receive an input from a pilot and to output a primary control signal and a primary transmission path connected to the primary controller and configured to relay the primary control signal. The flight control system may also include a backup controller configured to receive the input from the pilot and to output a backup control signal and a backup transmission path connected to the backup controller and configured to relay the backup control signal. Additionally, the flight control system may include an actuator having a remote electronics unit configured to receive the primary control signal and the backup control signal and to determine if the primary control signal is available and valid.Type: GrantFiled: January 17, 2007Date of Patent: July 26, 2011Assignee: Gulfstream Aerospace CorporationInventor: Jukka Matti Hirvonen
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Patent number: 7878461Abstract: Embodiments of the invention relate to a flight control system for controlling an aircraft in flight having a backup control system integrated into an active control stick. The actuated control stick may include a processing unit that includes independent and separate hardware and/or software dedicated to the primary control system and the backup control system. For the primary control system, the processing unit may receive a sensed primary control stick signal and communicate with a primary processor, which may be configured to generate a primary control signal. For the backup control system, the processing unit may receive a sensed backup control stick signal and generate a backup control signal. The processing unit may also generate tactile signal for use by the actuated control stick to adjust the feel of a pilot's control stick.Type: GrantFiled: January 17, 2007Date of Patent: February 1, 2011Assignee: Gulfstream Aerospace CorporationInventors: Jukka Matti Hirvonen, Gary Palfreyman
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Publication number: 20070164166Abstract: Embodiments of the invention relate to a flight control system for controlling an aircraft during flight. The flight control system may include a primary controller configured to receive an input from a pilot and to output a primary control signal and a primary transmission path connected to the primary controller and configured to relay the primary control signal. The flight control system may also include a backup controller configured to receive the input from the pilot and to output a backup control signal and a backup transmission path connected to the backup controller and configured to relay the backup control signal. Additionally, the flight control system may include an actuator having a remote electronics unit configured to receive the primary control signal and the backup control signal and to determine if the primary control signal is available and valid.Type: ApplicationFiled: January 17, 2007Publication date: July 19, 2007Inventor: Jukka Matti Hirvonen