| 摘要 |
The present invention pertains to an aircraft power management system comprising an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, at least one primary electrical equipment including a primary load and a bus bar switch, the primary load being coupled in parallel to the first power supply bus bar, and the bus bar switch being configured to selectively deactivate the first power supply bus bar downstream of the at least one primary electrical equipment, and at least one tertiary electrical equipment including a tertiary load being coupled to the first power supply bus bar downstream of the at least one primary electrical equipment, wherein the at least one primary electrical equipment further includes a load monitoring device configured to monitor the power demand of the primary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar, if the monitored power demand of the primary load exceeds a primary threshold. |
