公开(公告)号：US12240623B2

公开(公告)日：2025-03-04

申请号：US18184238

申请日：2023-03-15

Applicant: Eaton Intelligent Power Limited

Inventor： Stephen E. Sipprell

IPC: B64D37/32

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.

公开(公告)号：US11618582B2

公开(公告)日：2023-04-04

申请号：US16835540

申请日：2020-03-31

Applicant: Eaton Intelligent Power Limited

Inventor： Stephen E. Sipprell

IPC: B64D37/32

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.

公开(公告)号：US20210380269A1

公开(公告)日：2021-12-09

申请号：US17337697

申请日：2021-06-03

Applicant: Eaton Intelligent Power Limited

Inventor： Stephen E. Sipprell

IPC: B64D37/32 ,  B64D13/08 ,  B64D13/02

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.

公开(公告)号：US12091184B2

公开(公告)日：2024-09-17

申请号：US17337697

申请日：2021-06-03

Applicant: Eaton Intelligent Power Limited

Inventor： Stephen E. Sipprell

IPC: B64D37/32 ,  B64D13/02 ,  B64D13/08 ,  B64C30/00 ,  B64D13/06

CPC classification number: B64D37/32 ,  B64D13/02 ,  B64D13/08 ,  B64C30/00 ,  B64D2013/0659 ,  B64D2037/325

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.

公开(公告)号：US20230294839A1

公开(公告)日：2023-09-21

申请号：US18184238

申请日：2023-03-15

Applicant: Eaton Intelligent Power Limited

Inventor： Stephen E. Sipprell

IPC: B64D37/32

CPC classification number: B64D37/32

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.

公开(公告)号：US11104448B2

公开(公告)日：2021-08-31

申请号：US16419285

申请日：2019-05-22

Applicant: Eaton Intelligent Power Limited

Inventor： Jason Miner ,  Stephen E. Sipprell

IPC: B64D39/06 ,  B67D7/00 ,  B67D7/32 ,  B67D7/42 ,  B67D7/04

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.

公开(公告)号：US20200307821A1

公开(公告)日：2020-10-01

申请号：US16835540

申请日：2020-03-31

Applicant: Eaton Intelligent Power Limited

Inventor： Stephen E. Sipprell

IPC: B64D37/32

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.