Abstract: A device for providing power or thrust to an aerospace vehicle with a control system providing two different mechanical power outputs deriving their power from one common mechanical power source unit includes: a common mechanical power source unit an adjustable mechanical load unit driven by the common mechanical power source unit, an electrical machine unit with a mechanical power interface connected to the common mechanical power source unit and configured to receive mechanical power from the common mechanical power source unit to provide electrical power at an electrical power interface, and a control system configured to receive a mechanical power or thrust demand and standard air data from the aerospace vehicle. Only based on the mechanical power or thrust demand and standard air data, the control system is configured to control the device to provide mechanical power or thrust as well as electrical power to the aerospace vehicle.