Patents by Inventor Stephen E. Sipprell

Stephen E. Sipprell 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).

  • Publication number: 20230294839
    Abstract: An aircraft fuel tank inerting system may include at least one fuel tank, at least one surge tank, an inert air assembly, at least one fluid valve connected to the at least one fuel tank, the at least one surge tank, and the inert air assembly, and/or an electronic control unit. The electronic control unit may control the at least one fluid valve to provide inert air from the inert air assembly to the at least one fuel tank and/or to the at least one surge tank. The electronic control unit may control the at least one fluid valve to provide inert air from the inert air assembly to the fuel tank during a climb phase of a flight and control the at least one fluid valve to provide inert air from the inert air assembly to the at least one surge tank during a descent phase of the flight.
    Type: Application
    Filed: March 15, 2023
    Publication date: September 21, 2023
    Inventor: Stephen E. Sipprell
  • Patent number: 11618582
    Abstract: An aircraft fuel tank inerting system may include at least one fuel tank, at least one surge tank, an inert air assembly, at least one fluid valve connected to the at least one fuel tank, the at least one surge tank, and the inert air assembly, and/or an electronic control unit. The electronic control unit may control the at least one fluid valve to provide inert air from the inert air assembly to the at least one fuel tank and/or to the at least one surge tank. The electronic control unit may control the at least one fluid valve to provide inert air from the inert air assembly to the fuel tank during a climb phase of a flight and control the at least one fluid valve to provide inert air from the inert air assembly to the at least one surge tank during a descent phase of the flight.
    Type: Grant
    Filed: March 31, 2020
    Date of Patent: April 4, 2023
    Assignee: Eaton Intelligent Power Limited
    Inventor: Stephen E. Sipprell
  • Publication number: 20210380269
    Abstract: A fuel tank inerting system includes a cabin air source, a conduit, a heat exchanger, and a pressurized air source. In embodiments, the pressurized air source is configured to provide pressurized air to the heat exchanger, and the conduit is configured to provide cabin air from the cabin air source to the heat exchanger.
    Type: Application
    Filed: June 3, 2021
    Publication date: December 9, 2021
    Inventor: Stephen E. Sipprell
  • Patent number: 11104448
    Abstract: A fluid nozzle includes an inlet housing configured for connection with a tanker aircraft boom, an outlet housing connected with the inlet and configured for connection with a receiving aircraft receptacle, and/or a sensor configured for determining at least one of a ready status, a contact status, and an articulation angle. The sensor may include a ready sensor, a contact sensor, and/or an articulation angle sensor. A method of connecting a fluid nozzle with a receptacle may include providing a fluid nozzle, providing a receptacle, moving the fluid nozzle toward the receptacle, sensing contact between the fluid nozzle and the receptacle via a contact sensor, and/or sensing, via a ready sensor, that the receptacle is latched with the fluid nozzle.
    Type: Grant
    Filed: May 22, 2019
    Date of Patent: August 31, 2021
    Assignee: Eaton Intelligent Power Limited
    Inventors: Jason Miner, Stephen E. Sipprell
  • Publication number: 20200307821
    Abstract: An aircraft fuel tank inerting system may include at least one fuel tank, at least one surge tank, an inert air assembly, at least one fluid valve connected to the at least one fuel tank, the at least one surge tank, and the inert air assembly, and/or an electronic control unit. The electronic control unit may control the at least one fluid valve to provide inert air from the inert air assembly to the at least one fuel tank and/or to the at least one surge tank. The electronic control unit may control the at least one fluid valve to provide inert air from the inert air assembly to the fuel tank during a climb phase of a flight and control the at least one fluid valve to provide inert air from the inert air assembly to the at least one surge tank during a descent phase of the flight.
    Type: Application
    Filed: March 31, 2020
    Publication date: October 1, 2020
    Inventor: Stephen E. Sipprell
  • Publication number: 20190359473
    Abstract: A fluid nozzle includes an inlet housing configured for connection with a tanker aircraft boom, an outlet housing connected with the inlet and configured for connection with a receiving aircraft receptacle, and/or a sensor configured for determining at least one of a ready status, a contact status, and an articulation angle. The sensor may include a ready sensor, a contact sensor, and/or an articulation angle sensor. A method of connecting a fluid nozzle with a receptacle may include providing a fluid nozzle, providing a receptacle, moving the fluid nozzle toward the receptacle, sensing contact between the fluid nozzle and the receptacle via a contact sensor, and/or sensing, via a ready sensor, that the receptacle is latched with the fluid nozzle.
    Type: Application
    Filed: May 22, 2019
    Publication date: November 28, 2019
    Inventors: Jason Miner, Stephen E. Sipprell