Apparatus and systems for engine and generator control within an aircraft

A combined engine electronic controller (EEC)-generator control unit (GCU) module, comprising:

• a generator control unit (GCU) module configured to perform GCU functions to control a compound AC generator;
• and
• an engine electronic controller (EEC) module configured to perform EEC functions to control an engine, and
• wherein the combined EEC-GCU module is configured to be powered by a common AC power signal generated by a permanent magnet generator (PMG) of a compound AC generator.

An aircraft, comprising:

• a load;
• an engine;
• an engine electronic controller (EEC) module that is configured to control the engine;
• a compound AC generator comprising:
• a permanent magnet generator (PMG) configured to be driven by a shaft to generate an AC power signal;
• an excitation stage comprising:
• an excitation stator;
• and an excitation rotor that includes rotating diodes, wherein the excitation rotor is configured to generate an AC voltage output signal, and
• a power motor stage comprising:
• a power stator;
• and a power rotor is configured to generate, in response to the AC voltage output signal, a rotating field that induces a plurality of three-phase AC voltage output signals in the power stator, wherein the plurality of three-phase AC voltage output signals power the load;
• and
• a generator control unit (GCU) module that is configured to control the compound AC generator, wherein the GCU module and the EEC module are co-located within a combined EEC-GCU module such that the GCU module and the EEC module are both implemented within the combined EEC-GCU module, and
• wherein the PMG is directly coupled to the GCU module and the EEC module such that the compound AC generator is configured to simultaneously supply the AC power signal to the GCU module and to the EEC module to provide electrical power to the EEC module and to the GCU module.