| 摘要 |
A novel system and methodology of electrical power regulation, conditioning and distribution on an aircraft is disclosed. The system comprises an alternator adapted to directly connect to an engine on the aircraft and generate variable frequency AC power, a variable frequency AC bus coupled directly to the alternator, and at least one variable frequency AC load at low performance, coupled to the variable frequency AC bus. At least one bi-directional power converter may be coupled directly to the variable frequency AC bus and adapted to convert the variable frequency AC raw power to a fully regulated adjustable-frequency and adjustable-voltage power to control AC motors and other high performance variable frequency AC loads. A bi-directional power converter is coupled directly to the variable frequency AC bus and adapted to convert the variable frequency AC power generated by the alternator into constant frequency AC power. At least one constant frequency AC load is coupled to a constant frequency AC bus which is in turn coupled between the constant frequency AC load and the bi-directional power converter. A first bi-directional power bus controller is coupled between the bi-directional power converter and the constant frequency AC bus. The system further comprises an AC/DC bi-directional power converter coupled to a DC bus and at least one DC load coupled thereto. A second bi-directional power bus controller is coupled between the AC/DC power converter and the DC bus. The first and second bi-directional controllers provide for the selective and automatic reconfiguration of the flow of power through the system. A novel high-level subsystem interconnection architecture is also disclosed.
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