An isolated power management system, comprising at least one electronic power generator including: a stationary side having an exciter field stator winding, a main field stator winding, and an isolator stator winding; and a rotational side that is configured to rotate with respect to the stationary side, the rotational side including a rotor power converting unit; and at least one digital engine microcontroller that is configured to generate a first electrical excitation current and to excite the exciter field stator winding to generate a first electromagnetic field, the rotor power converting unit configured to generate a second electromagnetic field in response to being energized by the first electromagnetic field, wherein the main field stator winding and the isolator stator winding are configured to output first and second power signals, respectively, in response to being energized by the second electromagnetic field, characterized by a signal line that connects the isolator stator winding to the digital engine microcontroller wherein the isolator stator winding is configured to output the second power signal to the digital engine microcontroller and to power the digital controller via the second power signal, the second power signal being independent and isolated from the first power signal, wherein the first power signal powers an airframe (A/F) system of the aircraft, and wherein the at least one digital engine microcontroller (104a/104b) is powered by the second power signal, but separately from the main power signal that powers the airframe (A/F) system. at least one electronic power generator including: a stationary side having an exciter field stator winding, a main field stator winding, and an isolator stator winding; and a rotational side that is configured to rotate with respect to the stationary side, a stationary side having an exciter field stator winding, a main field stator winding, and an isolator stator winding; and a rotational side that is configured to rotate with respect to the stationary side, the rotational side including a rotor power converting unit; and at least one digital engine microcontroller that is configured to generate a first electrical excitation current and to excite the exciter field stator winding to generate a first electromagnetic field, the rotor power converting unit configured to generate a second electromagnetic field in response to being energized by the first electromagnetic field, wherein the main field stator winding and the isolator stator winding are configured to output first and second power signals, respectively, in response to being energized by the second electromagnetic field, characterized by a signal line that connects the isolator stator winding to the digital engine microcontroller wherein the isolator stator winding is configured to output the second power signal to the digital engine microcontroller and to power the digital controller via the second power signal, the second power signal being independent and isolated from the first power signal, wherein the first power signal powers an airframe (A/F) system of the aircraft, and wherein the at least one digital engine microcontroller (104a/104b) is powered by the second power signal, but separately from the main power signal that powers the airframe (A/F) system.