Bae Systems Controls Inc.

Matthew S Boecke

Arthur Paull Lyons

Brian Sehn

Brian S Sehn

An energy management system (EMS) for an aircraft is provided. The aircraft may have one of a plurality of propulsion systems such as a parallel hybrid electric propulsion system, a parallel turbo electric propulsion system, an electric propulsion system, a turbo electric propulsion system and a turbo hybrid electric propulsion system. The EMS comprises redundant control paths for controlling safety critical operation. Each redundant control path is configured to independently determine whether to electrically isolate a line replaceable unit (LRU) from a high voltage DC link (HVDC link) based on status information from the LRU. The isolation is based on the independent determination. The HVDC link is used for propulsion. The number of the redundant control paths and components may be depending on the type of the propulsion system.

Aircraft propulsion utilizing a safety critical energy management system

A hybrid electric vehicle having a controllable switch that enables a DC link to be operated independent from an energy storage system (ESS) is provided. The ESS is selectively couplable to the DC link via the controllable switch. A processor is configured to control the switch to open and close under certain conditions. When the switch is opened, the processor is configured to instruct an engine controller to cause an engine which is coupled to a generator to boost engine output. The generator is coupled to a generator inverter which is also coupled to the DC link. A motor inverter is also coupled to the DC link and is configured to provide AC power to the motor.

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Endicott, NY, United States of America

Matthew S Boecke