Abstract: 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.

Abstract: A lithium-ion battery assembly includes a plurality of battery cells in a spaced-apart and generally parallel arrangement, each cell of the battery cells extending along a central axis and having a first end portion with a negative terminal and a second end portion with a positive terminal. The assembly includes a first capture plate and a second capture plate, where at least the first capture plate defines capture plate openings corresponding to the plurality of battery cells, the first capture plate spaced from and oriented generally parallel to the second capture plate. Each of the plurality of battery cells extends between the first and second capture plates and is coaxially arranged with one of the capture plate openings in the first capture plate. The assembly optionally includes a body between the capture plates, the body defining a void for each battery cell.

Abstract: An electric machine and a turning gear system for aircraft gas turbine engines are provided. The system has an electric machine designed for dual mode operation and a controller. The stator winding arrangement in the electric machine enables operation in either generating mode, during normal flight or motoring mode, during active engine turning. The controller is configured to reconfiguration connections of the windings external to the electric machine.