Provided in this disclosure is a high voltage distribution system of an electric aircraft. The system includes a power source mechanically connected to an electric aircraft, where the power source is configured to supply power to the electric aircraft. The system also includes a flight component mechanically connected to the electric aircraft. The system also includes a distribution component configured to control the providing of power to and from the power source and the flight component as needed during recharging and/or operation of the electric aircraft.

Provided in this disclosure is a high voltage distribution system of an electric aircraft. The system includes a power source mechanically connected to an electric aircraft, where the power source is configured to supply power to the electric aircraft. The system also includes a flight component mechanically connected to the electric aircraft. The system also includes a distribution component configured to control the providing of power to and from the power source and the flight component as needed during recharging and/or operation of the electric aircraft.

A hybrid powertrain system and method includes a prime mover driving a generator/motor to produce an AC power output. The AC power output is applied to a rectifier which is controlled to transform the applied AC power to DC power to supply a DC Power bus at a selected voltage and current. An energy storage device is also connected to the DC power bus and the current flow between the energy storage device and the DC power bus is monitored and compared to preselected values and the results of that comparison are used to alter the operation of the rectifier to increase or decrease, as needed, the current provided to the DC power bus as electrical loads on the DC power bus change.

A propulsion system including: a fuel cell assembly comprising a fuel cell, the fuel cell defining an outlet positioned to remove output products from the fuel cell and a fuel cell assembly operating condition; a combustion section that includes a combustor configured to receive a flow of aviation fuel from the aircraft fuel supply and further configured to receive the output products from the fuel cell; and a controller comprising memory and one or more processors, the memory storing instructions that when executed by the one or more processors cause the propulsion system to perform operations including: determining data indicative of at least one of an enthalpy or a composition of the output products from the fuel cell; and modifying the flow of aviation fuel from the aircraft fuel supply to the combustor based on the at least one of the enthalpy or the composition of the output products.

A propulsion system including: a fuel cell assembly comprising a fuel cell, the fuel cell defining an outlet positioned to remove output products from the fuel cell and a fuel cell assembly operating condition; a combustion section that includes a combustor configured to receive a flow of aviation fuel from the aircraft fuel supply and further configured to receive the output products from the fuel cell; and a controller comprising memory and one or more processors, the memory storing instructions that when executed by the one or more processors cause the propulsion system to perform operations including: determining data indicative of at least one of an enthalpy or a composition of the output products from the fuel cell; and modifying the flow of aviation fuel from the aircraft fuel supply to the combustor based on the at least one of the enthalpy or the composition of the output products.

A safety management system for an aircraft, or a propulsion system thereof including a fuel cell assembly and a combustion engine, may include various sensors and controllers configured to execute a safety action. At least one sensor is configured to detect at least one operating parameter of the propulsion system, and a controller is configured to determine that the at least one operating parameter has achieved a safety threshold and to execute a safety action when the at least one operating parameter has achieved the safety threshold. The safety action is configured to control operation of the fuel cell assembly and to control operation of the combustion engine.

A safety management system for an aircraft, or a propulsion system thereof including a fuel cell assembly and a combustion engine, may include various sensors and controllers configured to execute a safety action. At least one sensor is configured to detect at least one operating parameter of the propulsion system, and a controller is configured to determine that the at least one operating parameter has achieved a safety threshold and to execute a safety action when the at least one operating parameter has achieved the safety threshold. The safety action is configured to control operation of the fuel cell assembly and to control operation of the combustion engine.

A propulsion system for an aircraft includes a fuel cell assembly, the fuel cell assembly including a fuel cell, and a turbomachine, the turbomachine including a compressor section, a combustor, and a turbine section arranged in serial flow order. The combustor is configured to receive a flow of fuel and further configured to receive output products from the fuel cell. A controller is configured to receive data indicative of an engine constraint of the turbomachine, determine that the engine constraint has achieved a fuel cell trim threshold; and perform a fuel cell corrective action with the fuel cell assembly in response to determining that the engine constraint has achieved the fuel cell trim threshold.

A propulsion system for an aircraft includes a fuel cell assembly, the fuel cell assembly including a fuel cell, and a turbomachine, the turbomachine including a compressor section, a combustor, and a turbine section arranged in serial flow order. The combustor is configured to receive a flow of fuel and further configured to receive output products from the fuel cell. A controller is configured to receive data indicative of an engine constraint of the turbomachine, determine that the engine constraint has achieved a fuel cell trim threshold; and perform a fuel cell corrective action with the fuel cell assembly in response to determining that the engine constraint has achieved the fuel cell trim threshold.

A method to modify an aircraft including: disconnecting a first engine control device from command cables and transmission cables, wherein the first engine control device is in a fuselage section forward of a pressure bulkhead; replacing the engine control device with a jumper connector positioned in the fuselage section, wherein the jumper connector electrically connects the command cables to the transmission cables; installing a second engine control device in the fuselage aft of the pressure bulkhead, wherein the second engine control device is in an engine compartment of the fuselage; connecting the second engine control device to transmission cables at a location at or near the pressure bulkhead; connecting sensor cabling directly to the second engine control device, and connecting the engine control device directly to the engine.