US 12,280,881 B2
Aircraft propulsion utilizing a safety critical energy management system
Matthew S. Boecke, Endicott, NY (US); and Arthur P. Lyons, Maine, NY (US)
Assigned to BAE Systems Controls Inc., Endicott, NY (US)
Filed by BAE Systems Controls Inc., Endicott, NY (US)
Filed on Jul. 14, 2023, as Appl. No. 18/352,763.
Claims priority of provisional application 63/389,599, filed on Jul. 15, 2022.
Prior Publication US 2024/0017844 A1, Jan. 18, 2024
Int. Cl. B64D 27/24 (2024.01); B64D 31/06 (2024.01); B64D 27/02 (2006.01)
CPC B64D 27/24 (2013.01) [B64D 31/06 (2013.01); B64D 27/026 (2024.01)] 23 Claims
OG exemplary drawing
 
1. An energy management system (EMS) for an aircraft, the EMS is configured to be connectable with a plurality of source line replaceable units (source LRUs) and a plurality of sink line replaceable units (sink LRUs), where a source LRU is a source of power for a high voltage DC link used for propulsion and a sink LRU uses the power from the high voltage DC link for propulsion, the EMS comprising:
communication interfaces configured to receive status information from each of the source LRUs and sink LRUs, the status information comprising information from respective sensors within the respective LRU and a determination that the information from each sensor is within a predetermined range; and to transmit commands to the source LRUs and the sink LRUs; and
redundant control paths for controlling safety critical operations, the redundant control paths being configured to independently determine whether to electrically isolate a LRU from the high voltage DC link based on the status information from the LRU, wherein isolation is based on the independent determination;
wherein the redundant control paths also comprises a second control path, where the second control path comprises a human machine interface in a control cabin in the aircraft to display the status information and receive a command to isolate an LRU.