Patents by Inventor Kevin Benning

Kevin Benning 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).

  • Patent number: 11168883
    Abstract: A vented module includes a housing portion having a drainage side and a drainage port within the drainage side. The module further includes a flame arrestor including a first surface having a fluid inlet, a second surface having at least one fluid outlet, a labyrinth channel extending from the fluid inlet to the fluid outlet, and at least one mesh screen disposed within the labyrinth channel. The flame arrestor is attached to the housing portion such that the drainage port is aligned with the fluid inlet.
    Type: Grant
    Filed: September 29, 2017
    Date of Patent: November 9, 2021
    Assignee: Rosemount Aerospace Inc.
    Inventors: Kevin Benning, Aaron Wesser, Scott Wigen, Andrew Sherman
  • Patent number: 10852316
    Abstract: A system includes an air data computer (ADC) having a single pneumatic port for receiving a pneumatic input, a plurality of electrical inputs for receiving one or more electrical signals, and an output. The ADC can transmit, via the output, air data parameters based on the received pneumatic input and the received one or more electrical signals. In a further example embodiment, the system includes a first pressure sensing probe discrete from the ADC and a pneumatic connection joining a pressure sensing port of the first probe to the pneumatic input of the ADC. Second and third pressure sensing probes pneumatically coupled to respective pressure modules, which output electrical signals to the ADC, the electrical signals being representative of pressures sensed by the second and third pressure sensing probes, respectively.
    Type: Grant
    Filed: June 15, 2018
    Date of Patent: December 1, 2020
    Assignee: Rosemount Aerospace Inc.
    Inventors: Brian Brent Naslund, Joel Boelke, Benjamin John Langemo, Kevin Benning
  • Publication number: 20190383847
    Abstract: A system includes an air data computer (ADC) having a single pneumatic port for receiving a pneumatic input, a plurality of electrical inputs for receiving one or more electrical signals, and an output. The ADC can transmit, via the output, air data parameters based on the received pneumatic input and the received one or more electrical signals. In a further example embodiment, the system includes a first pressure sensing probe discrete from the ADC and a pneumatic connection joining a pressure sensing port of the first probe to the pneumatic input of the ADC. Second and third pressure sensing probes pneumatically coupled to respective pressure modules, which output electrical signals to the ADC, the electrical signals being representative of pressures sensed by the second and third pressure sensing probes, respectively.
    Type: Application
    Filed: June 15, 2018
    Publication date: December 19, 2019
    Inventors: Brian Brent Naslund, Joel Boelke, Benjamin John Langemo, Kevin Benning
  • Publication number: 20190101284
    Abstract: A vented module includes a housing portion having a drainage side and a drainage port within the drainage side. The module further includes a flame arrestor including a first surface having a fluid inlet, a second surface having at least one fluid outlet, a labyrinth channel extending from the fluid inlet to the fluid outlet, and at least one mesh screen disposed within the labyrinth channel. The flame arrestor is attached to the housing portion such that the drainage port is aligned with the fluid inlet.
    Type: Application
    Filed: September 29, 2017
    Publication date: April 4, 2019
    Inventors: Kevin Benning, Aaron Wesser, Scott Wigen, Andrew Sherman
  • Publication number: 20190064198
    Abstract: An aircraft air data system includes a first air data probe disposed on a first side of the aircraft, a second air data probe disposed on a second side of the aircraft, a first plurality of static pressure sensing ports disposed on the first side of the aircraft, and a second plurality of static pressure ports disposed on the second side of the aircraft. Each of the first air data probe and the second air data probe include a barrel portion configured to extend into an oncoming airflow, a total pressure sensing port, and an integrated total pressure sensor. Each of the first plurality of static pressure sensing ports is connected to one of a first plurality of integrated static pressure sensors. Each of the second plurality of static pressure sensing ports is connected to one of a second plurality of integrated static pressure sensors.
    Type: Application
    Filed: August 24, 2017
    Publication date: February 28, 2019
    Inventors: Ronald Fritz Liffrig, Brian Brent Naslund, Kevin Benning
  • Patent number: 10132824
    Abstract: A system includes a device having a first surface configured to be exposed to airflow about an exterior of an aircraft, the device including a first self-compensating heater configured to heat the first surface, a first current monitor configured to sense a first measurement value representing electrical current flow through the first self-compensating heater, one or more processors, and computer-readable memory encoded with instructions that, when executed by the one or more processors, cause the system to receive aircraft flight condition data and produce an icing condition signal based upon the first measurement value and the aircraft flight condition data.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: November 20, 2018
    Assignee: Rosemount Aerospace Inc.
    Inventors: Kevin Benning, Weston Daniel Clarence Heuer
  • Patent number: 10048288
    Abstract: An angle of attack sensing system includes a rotatable vane, a first pressure sensing port, a second pressure sensing port, a vane position sensor, and a fault detector. The rotatable vane includes a first surface and a second surface opposite the first surface. The first pressure sensing port is disposed in the first surface. The second pressure sensing port is disposed in the second surface. The vane position sensor is configured to output a rotational position signal of the rotatable vane. The fault detector is configured to output an indication of a rotational fault condition based on a difference between a first sensed pressure from the first pressure sensing port and a second sensed pressure from the second pressure sensing port.
    Type: Grant
    Filed: January 8, 2016
    Date of Patent: August 14, 2018
    Assignee: Rosemount Aerospace Inc.
    Inventor: Kevin Benning
  • Publication number: 20170370960
    Abstract: A system includes a device having a first surface configured to be exposed to airflow about an exterior of an aircraft, the device including a first self-compensating heater configured to heat the first surface, a first current monitor configured to sense a first measurement value representing electrical current flow through the first self-compensating heater, one or more processors, and computer-readable memory encoded with instructions that, when executed by the one or more processors, cause the system to receive aircraft flight condition data and produce an icing condition signal based upon the first measurement value and the aircraft flight condition data.
    Type: Application
    Filed: June 16, 2017
    Publication date: December 28, 2017
    Inventors: Kevin Benning, Weston Daniel Clarence Heuer
  • Publication number: 20170199218
    Abstract: An angle of attack sensing system includes a rotatable vane, a first pressure sensing port, a second pressure sensing port, a vane position sensor, and a fault detector. The rotatable vane includes a first surface and a second surface opposite the first surface. The first pressure sensing port is disposed in the first surface. The second pressure sensing port is disposed in the second surface. The vane position sensor is configured to output a rotational position signal of the rotatable vane. The fault detector is configured to output an indication of a rotational fault condition based on a difference between a first sensed pressure from the first pressure sensing port and a second sensed pressure from the second pressure sensing port.
    Type: Application
    Filed: January 8, 2016
    Publication date: July 13, 2017
    Inventor: Kevin Benning
  • Publication number: 20070064766
    Abstract: A total air temperature probe for measuring total air temperature includes a head having an airflow inlet, a main airflow exit, and a flow separation bend positioned between the airflow inlet and the main airflow exit. A plurality of bleed holes are in the flow separation bend. A bleed port air exit is coupled to the plurality of bleed holes. The head geometry is configured to provide enhanced deicing heater error (DHE) performance.
    Type: Application
    Filed: September 20, 2005
    Publication date: March 22, 2007
    Applicant: Rosemount Aerospace Inc.
    Inventors: Kevin Benning, Fred Steffen, Charles Willcox