Patent ID: 8288885
Filing Date: 2012-10-16
Classification: B64D,H02P,Y02T

Abstract:
1. A power system for an aircraft comprising: electromechanical control surface actuators adapted to either consume electrical power during operation or regenerate electrical power during operation; a prime mover providing power to mechanical power loads; an electrical machine that either converts mechanical energy from the prime mover to electrical energy or converts electrical energy to supply mechanical energy to the prime mover; and a bidirectional inverter converter controller (ICC) that converts power between the electrical machine and a power bus and controls power flow between the power bus and the electric machine, wherein the power bus is a bidirectional bus that delivers power between the ICC and the control surface actuators and between the ICC and ancillary electrical loads of the aircraft, wherein the ICC transmits electrical power from the electrical machine to the bus when power consumption of the control surface actuators and the ancillary loads is positive, wherein the ICC transmits electrical power to the ancillary electrical loads when the control surface actuators regenerate electrical power, and wherein the ICC transmits portions of the electrical power regenerated by the control surface actuators to the electrical machine when the regenerated power exceeds power consumption of the ancillary loads.