公开(公告)号：US12116141B2

公开(公告)日：2024-10-15

申请号：US17545566

申请日：2021-12-08

Applicant: Eaton Intelligent Power Limited

Inventor： Jeffrey A. Baker ,  Mario F. Cruz ,  David R. Smit ,  Derek Paul Dougherty

IPC: B64D41/00

CPC classification number: B64D41/00 ,  B64D2201/00 ,  B64D2221/00

Abstract: An aircraft emergency power unit (EPU) includes a battery powered subsystem that replaces toxic hydrazine fuel use. The battery of the battery powered subsystem is utilized to supply power to an aircraft electrical system in the event of a failure of the EPU turbine-powered generator. The battery of the battery powered subsystem is also utilized to supply power to an electric hydraulic motor pump in the event of a failure of the EPU turbine-powered hydraulic pump (or to augment the output of the EPU-turbine-powered hydraulic pump). The battery of the battery powered subsystem is capable of simultaneously powering the electrical system and the electric hydraulic motor pump or of powering either one of the electrical system and electric hydraulic motor pump independently based upon aircraft fault conditions. Intermittent operation of the electrical system and/or the electric hydraulic motor pump in an intermittent fashion on an as-needed basis is also possible.

公开(公告)号：US20220185496A1

公开(公告)日：2022-06-16

申请号：US17545566

申请日：2021-12-08

Applicant: Eaton Intelligent Power Limited

Inventor： Jeffrey A. Baker ,  Mario F. Cruz ,  David R. Smit ,  Derek Paul Dougherty

IPC: B64D41/00

Abstract: An aircraft emergency power unit (EPU) includes a battery powered subsystem that replaces toxic hydrazine fuel use. The battery of the battery powered subsystem is utilized to supply power to an aircraft electrical system in the event of a failure of the EPU turbine-powered generator. The battery of the battery powered subsystem is also utilized to supply power to an electric hydraulic motor pump in the event of a failure of the EPU turbine-powered hydraulic pump (or to augment the output of the EPU-turbine-powered hydraulic pump). The battery of the battery powered subsystem is capable of simultaneously powering the electrical system and the electric hydraulic motor pump or of powering either one of the electrical system and electric hydraulic motor pump independently based upon aircraft fault conditions. Intermittent operation of the electrical system and/or the electric hydraulic motor pump in an intermittent fashion on an as-needed basis is also possible.