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公开(公告)号：US20220356875A1
公开(公告)日：2022-11-10
申请号：US17737619
申请日：2022-05-05
Applicant: Eaton Intelligent Power Limited
Inventor： Joshua Boone Pepper , David E. Korba , Brady Powell Dearing , Eugene Mikhailovich Grigoriev , Kelly Dale Valtr , Stephen Marshall Devan
Abstract: The present disclosure relates to a hydraulic power pack arrangement that can be configured in multiple different mounting configurations. The hydraulic power pack arrangement can include a bracket assembly for mounting a hydraulic power pack core assembly and a hydraulic reservoir assembly at a mounting location such as a floor, wall, or ceiling of an aircraft.
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Patent Agency Ranking
公开(公告)号：US11821419B2
公开(公告)日：2023-11-21
申请号：US17737619
申请日：2022-05-05
Applicant: Eaton Intelligent Power Limited
Inventor： Joshua Boone Pepper , David E. Korba , Brady Powell Dearing , Eugene Mikhailovich Grigoriev , Kelly Dale Valtr , Stephen Marshall Devan
CPC classification number: F04B53/22 , F04B17/03 , F04B23/025 , F04B53/003 , F04B53/06 , F04B53/20
Abstract: The present disclosure relates to a hydraulic power pack arrangement that can be configured in multiple different mounting configurations. The hydraulic power pack arrangement can include a bracket assembly for mounting a hydraulic power pack core assembly and a hydraulic reservoir assembly at a mounting location such as a floor, wall, or ceiling of an aircraft.
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公开(公告)号：US20220169367A1
公开(公告)日：2022-06-02
申请号：US17538721
申请日：2021-11-30
Applicant: Eaton Intelligent Power Limited
Inventor： Joshua Boone Pepper , Brady Powell Dearing
Abstract: The left and right main landing gears on an aircraft are normally controlled by separate hydraulic power packs (HPP). Each HPP is sized for the load of the respective main landing gear. During failure of one of the HPP, a backup valve actuates to allow the other HPP to operate both main landing gears. With the backup valve actuated, the pump of the functioning HPP is coupled to the reservoirs of both HPPs and to the load paths to both main landing gears.
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公开(公告)号：US20240318646A1
公开(公告)日：2024-09-26
申请号：US18613590
申请日：2024-03-22
Applicant: Eaton Intelligent Power Limited
Inventor： Brady Powell Dearing , Stephen Marshall Devan , Kelly Dale Valtr , Joshua Boone Pepper , Derek Paul Dougherty , Douglas Alexander Scott , Joseph Spaniol
CPC classification number: F04B49/065 , F04B23/04 , F04B49/08 , F04B2201/1201 , F04B2203/0209 , F04B2207/042
Abstract: Systems and methods for electronic pressure control of pumps in a dual pump system. The system may include a controller, a primary pump operated by the controller to maintain a system pressure in a flow path at a first pressure setpoint; a pressure transducer reading the system pressure and providing the system pressure to the controller; and a secondary pump operated by the controller to maintain the system pressure at a second pressure setpoint, the second pressure setpoint being less that the first pressure setpoint.
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公开(公告)号：US12049302B2
公开(公告)日：2024-07-30
申请号：US17538721
申请日：2021-11-30
Applicant: Eaton Intelligent Power Limited
Inventor： Joshua Boone Pepper , Brady Powell Dearing
CPC classification number: B64C25/22 , F15B1/26 , F15B13/028 , F15B19/00 , F15B2211/20576 , F15B2211/426
Abstract: The left and right main landing gears on an aircraft are normally controlled by separate hydraulic power packs (HPP). Each HPP is sized for the load of the respective main landing gear. During failure of one of the HPP, a backup valve actuates to allow the other HPP to operate both main landing gears. With the backup valve actuated, the pump of the functioning HPP is coupled to the reservoirs of both HPPs and to the load paths to both main landing gears.
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公开(公告)号：US20240141892A1
公开(公告)日：2024-05-02
申请号：US18488335
申请日：2023-10-17
Applicant: Eaton Intelligent Power Limited
Inventor： Joshua Boone Pepper , David E. Korba , Brady Powell Dearing , Eugene Mikhailovich Grigoriev , Kelly Dale Valtr , Stephen Marshall Devan
CPC classification number: F04B53/22 , F04B17/03 , F04B23/025 , F04B53/003 , F04B53/06 , F04B53/20
Abstract: The present disclosure relates to a hydraulic power pack arrangement that can be configured in multiple different mounting configurations. The hydraulic power pack arrangement can include a bracket assembly for mounting a hydraulic power pack core assembly and a hydraulic reservoir assembly at a mounting location such as a floor, wall, or ceiling of an aircraft.
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