Patent ID: 8061650

Claim:
An aircraft power system, comprising: at least one aircraft primary power source; an aircraft auxiliary power unit; an electrical power circuit coupled to the at least one aircraft primary power source and the aircraft auxiliary power unit; a detection system operatively coupled to the electrical power circuit to provide a first signal corresponding to a load on the electrical power circuit, and a second signal corresponding to the power supplied to the electrical power circuit; and a controller coupled to the detection system and the auxiliary power unit, the controller being configured to: receive the first and second signals; and (a) if the first signal corresponds to a load that exceeds a first threshold level, and the auxiliary power unit is not started, automatically direct the auxiliary power unit to start after a delay; (b) if the first signal corresponds to a load that is below the first threshold level, and the auxiliary power unit is started, automatically direct the auxiliary power unit to stop after a delay; (c) if the second signal corresponds to a power that is below a second threshold level, and the auxiliary power unit is not started, automatically direct the auxiliary power unit to start after a delay; and (d) if the second signal corresponds to a power that is above the second threshold level, and the auxiliary power unit is started, automatically direct the auxiliary power unit to stop after a delay.