Adaptive aircraft electrical power distribution system

An adaptive aircraft electrical power distribution system, comprising:

• an engine generator disposed within an aircraft, the engine generator operable to generate and supply electrical power;
• a power connector mounted on a fuselage of the aircraft;
• an aircraft power distribution bus disposed within the aircraft and operable to distribute electrical power to an aircraft electrical load;
• and
• a bidirectional power controller mounted in the aircraft and electrically coupled to the engine generator, the aircraft power connector, and the aircraft power distribution bus, the bidirectional power controller configured to:
• sense when the engine generator is generating and supplying electrical power,
• sense when electrical power is being supplied to the power connector from an external power source,
• electrically couple the engine generator to the power connector when (i) the engine generator is generating and supplying electrical power and (ii) electrical power is not being supplied to the power connector from an external power source,
• electrically couple the power connector to the aircraft power distribution system when (i) the engine generator is not generating and supplying electrical power and (ii) electrical power is being supplied to the power connector from an external power source, and
• electrically couple the power connector to the aircraft power distribution system when (i) the engine generator is generating and supplying electrical power and (ii) electrical power is simultaneously being supplied to the power connector from an external power source.

An aircraft, comprising:

• a fuselage;
• an engine generator disposed within the fuselage and operable to generate and supply electrical power;
• a power connector mounted on the fuselage;
• an aircraft power distribution bus disposed within the fuselage and operable to distribute electrical power to an aircraft electrical load;
• and
• a bidirectional power controller mounted within the fuselage and electrically coupled to the engine generator, the aircraft power connector, and the aircraft power distribution bus, the bidirectional power controller configured to:
• sense when the engine generator is generating and supplying electrical power,
• sense when electrical power is being supplied to the power connector from an external power source,
• electrically couple the engine generator to the power connector when (i) the engine generator is generating and supplying electrical power and (ii) electrical power is not being supplied to the power connector from an external power source,
• electrically couple the power connector to the aircraft power distribution system when (i) the engine generator is not generating and supplying electrical power and (ii) electrical power is being supplied to the power connector from an external power source, and
• electrically couple the power connector to the aircraft power distribution system when (i) the engine generator is generating and supplying electrical power and (ii) electrical power is simultaneously being supplied to the power connector from an external power source.