Patent ID: 8789791
Filing Date: 2014-07-29
Classification: B64C,B64D,H02J,Y02T

Abstract:
1. An aircraft electrical system for an aircraft having a plurality of electrically actuated aerodynamic control surfaces, comprising: a plurality of electrically powered aircraft flight control actuators each including an electric motor operably coupled thereto and each positioned to move one of the plurality of aerodynamic control surfaces; one or more electrical distribution unit buses operably electrically coupled to the plurality of electrically powered aircraft flight control actuators; and a bidirectional electrical accumulator in electrical communication with the plurality of flight control actuators through the one or more electrical distribution unit buses, and positioned and configured to absorb excess electrical power regenerated by the plurality of flight control actuators and positioned and configured to provide supplemental power to the plurality of flight control actuators to thereby satisfy transient power requirements, the bidirectional accumulator comprising one or more power controllers and one or more energy storage devices, the one or more power controllers configured to maintain a voltage of each of the one or more energy storage devices and to manage a voltage between the one or more energy storage devices and the one or more electrical distribution unit buses to provide for charging the one or more energy storage devices, when not encountering transient or supplemental power requirements, the one or more power controllers in conjunction with the one or more energy storage devices configured to absorb the excess electrical power and transient voltages regenerated by the plurality of electrically powered flight control actuators defining a buck capability, and to provide the supplemental power to the plurality of electrically powered flight control actuators when encountering the transient or supplemental power requirements defining a boost capability.