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An electrical system for driving flight control actuators, electrical accumulator, and methods for managing electrical power for an aircraft electrical system and methods of retrofitting an aircraft electrical system with an electrical accumulator are provided. The electrical system can include a bi

An electrical system for driving flight control actuators, electrical accumulator, and methods for managing electrical power for an aircraft electrical system and methods of retrofitting an aircraft electrical system with an electrical accumulator are provided. The electrical system can include a bidirectional accumulator positioned in electrical communication with the plurality of flight control actuators to absorb excess electrical power regenerated by the plurality of flight control actuators and to provide supplemental power to the plurality of flight control actuators to thereby satisfy transient power requirements.

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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 th

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; anda 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. 2. The aircraft electrical system as defined in claim 1, wherein the electrical system includes a primary aircraft engine driven generator or fuel cell configured to provide continuous power, and wherein the bidirectional electrical accumulator is configured to absorb transient voltages beyond that capable of being absorbed under maximum continuous conditions by the aircraft electrical system without a regenerative resister and to satisfy transient power requirements beyond that capable of being supplied under maximum continuous conditions by the engine driven generator or fuel cell; andwherein the one or more power controllers is configured to maintain the voltage of each of the one or more devices below the desired continuous voltage maintained on the one or more electrical distribution unit buses. 3. The aircraft electrical system as defined in claim 1, wherein the one or more energy storage devices of the bidirectional electrical accumulator includes a first energy storage device comprising an ultracapacitor having a minimum rating of 25 kilowatts, and a second energy storage device comprising a lithium ion battery having a minimum rating of 2.5 amp-hours. 4. The aircraft electrical system as defined in claim 1, wherein the one or more energy storage devices of the bidirectional electrical accumulator includes: a first energy storage device positioned to absorb excess electrical power regenerated by the plurality of flight control actuators and to provide supplemental power to the plurality of control actuators to thereby satisfy transient power requirements; anda second energy storage device positioned to redundantly absorb peak excess electrical power regenerated by the plurality of control actuators when not sufficiently absorbed by the first energy storage device and to redundantly provide supplemental power to the plurality of control actuators when not sufficiently provided by the first energy storage device. 5. The aircraft electrical system as defined in claim 1, wherein the plurality of flight control actuators is a first plurality of flight control actuators, wherein the aircraft electrical system further comprises a second plurality of electrically actuated flight control actuators each including an electrical motor operably coupled thereto, and wherein the one or more energy storage devices of the bidirectional electrical accumulator includes a first energy storage device and a second energy storage device: the first energy storage device positioned to absorb excess electrical power regenerated by the first plurality of flight control actuators and to provide supplemental power to the first plurality of control actuators to thereby satisfy transient power requirements, and to redundantly absorb peak excess electrical power regenerated by the second plurality of flight control actuators when not sufficiently absorbed by the second energy storage device and to redundantly provide supplemental power to the second plurality of flight control actuators when not sufficiently provided by the second energy storage device; andthe second energy storage device positioned to absorb excess electrical power regenerated by the second plurality of flight control actuators and to provide supplemental power to the second plurality of control actuators to thereby satisfy transient power requirements, and positioned to redundantly absorb peak excess electrical power regenerated by the first plurality of control actuators when not sufficiently absorbed by the first energy storage device and to redundantly provide supplemental power to the first plurality of control actuators when not sufficiently provided by the first energy storage device. 6. A vehicle electrical system, comprising: a plurality of electrically powered vehicle control actuators each including an electric motor operably coupled thereto; a first vehicle electrical bus positioned in electrical communication with the plurality of flight control actuators, anda second vehicle electrical bus positioned in electrical communication with the plurality of flight control actuators; anda bidirectional electrical accumulator positioned in electrical communication with the plurality of control actuators and configured to provide power thereto and to receive power therefrom, to absorb regenerative power for the first electrical bus sufficient to maintain bus voltage within maximum continuous bus ratings thereof and to absorb regenerative power for the second electrical bus sufficient to maintain bus voltage within maximum continuous bus ratings thereof, the bidirectional electrical accumulator including: a first energy storage device positioned in electrical communication with the first vehicle electrical bus and configured to provide power to each of the plurality of flight control actuators and to receive and absorb excess electrical power regenerated by the plurality of control actuators and to provide supplemental power to the plurality of control actuators,a second energy storage device positioned in electrical communication with the second vehicle electrical bus to redundantly provide power to each of the plurality of flight control actuators and to redundantly receive and absorb peak excess electrical power regenerated by the plurality of control actuators and to redundantly provide supplemental power to the plurality of control actuators,a first power converter in communication with the first vehicle electrical bus and the first energy storage device to match and regulate voltage between the first energy storage device and the first vehicle electrical bus, the first energy storage device in combination with the first power converter configured to absorb the regenerative power sufficient to maintain bus voltage of the first vehicle electrical bus within maximum continuous bus ratings, anda second power converter in communication with the second vehicle electrical bus and the second energy storage device and configured to match and regulate voltage between the second energy storage device and the second vehicle electrical bus, the second energy storage device in combination with the second power converter configured to absorb the regenerative power sufficient to maintain bus voltage of the second vehicle electrical bus within maximum continuous bus ratings. 7. The vehicle electrical system as defined in claim 6, wherein the vehicle is an aircraft having an engine driven generator, and wherein the first energy storage device is positioned and configured to absorb transient voltages beyond that capable of being absorbed under maximum continuous conditions by the vehicle electrical system without a regenerative absorption device and to satisfy transient power requirements beyond that capable of being supplied under maximum continuous conditions by the engine driven generator;wherein the first power converter is configured to maintain the voltage the first energy storage device below the desired continuous voltage maintained on the first of vehicle electrical bus; andwherein the second power converter is configured to maintain the voltage of the second energy storage device allows the desired continuous voltage maintained on the second vehicle electrical bus. 8. The vehicle electrical system as defined in claim 6, wherein the first energy storage device comprises an ultracapacitor having a minimum rating of 25 kilowatts, and wherein the second energy storage device comprises a lithium ion battery having a minimum rating of 2.5 amp-hours. 9. The vehicle electrical system as defined in claim 6, wherein the vehicle is an aircraft having a plurality of aerodynamic control surfaces;wherein the plurality of vehicle control actuators is a plurality of aircraft flight control actuators each positioned to move one of the plurality of aerodynamic control surfaces;where the first vehicle electrical bus is a first direct current (DC) bus;wherein the second vehicle electrical bus is a second DC bus;wherein the first power converter is a DC-DC power converter; andwherein the second power converter is a second DC-DC power converter. 10. The vehicle electrical system as defined in claim 9, wherein the first energy storage device comprises a capacitor having a minimum rating of 25 kilowatts, and wherein the second energy storage device comprises a capacitor having a minimum rating of 25 kilowatts and a battery having a minimum rating of 2.5 amp-hours. 11. The vehicle electrical system as defined in claim 9, wherein the plurality of aircraft flight control actuators is a first plurality of flight control actuators;wherein the system further comprises a second plurality of electrically actuated vehicle flight control actuators each including an electrical motor operably coupled thereto;wherein the second energy storage device and the second vehicle DC bus are positioned in electrical communication with the second plurality of flight control actuators to provide power to each of the second plurality of flight control actuators and to receive power regenerated by the second plurality of flight control actuators; andwherein the first energy storage device and the first vehicle DC bus are positioned in electrical communication with the second plurality of flight control actuators to redundantly provide power to each of the second plurality of flight control actuators and to redundantly receive power regenerated by the second plurality of flight control actuators. 12. The vehicle electrical system as defined in claim 6, wherein the first energy storage device comprises an ultracapacitor, and wherein the second energy storage device comprises a lithium ion battery. 13. The aircraft electrical system as defined in claim 1, wherein the plurality of flight control actuators is a first plurality of flight control actuators;wherein the aircraft electrical system further comprises a second plurality of flight control actuators;wherein the one or more energy storage devices of the bidirectional electrical accumulator includes: a first energy storage device electrically coupled to the first plurality of flight control actuators and redundantly coupled to a second plurality of flight control actuators, anda second energy storage device electrically coupled to the second plurality of flight control actuators and redundantly coupled to the first plurality of flight control actuators;wherein the first energy storage device in conjunction with the one or more controllers is configured to absorb the excess electrical power regenerated by the first plurality of flight control actuators, and to absorb the excess electrical power regenerated by the second plurality of flight control actuators when not sufficiently absorbed by the second energy storage device, andwherein second first energy storage device in conjunction with the one or more controllers is configured to absorb the excess electrical power regenerated by the second plurality of flight control actuators, and to absorb the excess electrical power regenerated by the first plurality of flight control actuators when not sufficiently absorbed by the first energy storage device. 14. The aircraft electrical system as defined in claim 1, wherein the one or more electrical distribution unit buses comprises a first vehicle direct current (DC) bus positioned in electrical communication with the plurality of flight control actuators, anda second vehicle DC bus positioned in electrical communication with the second plurality of flight control actuators; andwherein the one or more energy storage devices comprises: a first energy storage device positioned in electrical communication with the first vehicle DC bus and configured to provide power to each of the plurality of flight control actuators and to receive and absorb excess electrical power regenerated by the plurality of control actuators and to provide supplemental power to the plurality of control actuators, anda second energy storage device positioned in electrical communication with the second vehicle DC bus to redundantly provide power to each of the plurality of flight control actuators and to redundantly receive and absorb peak excess electrical power regenerated by the plurality of control actuators and to redundantly provide supplemental power to the plurality of control actuators,wherein the one or more power converters comprises: a first DC-DC power converter in communication with the first vehicle DC bus and the first energy storage device to match and regulate voltage between the second energy storage device and the first vehicle DC bus, the first energy storage device in combination with the first DC-DC power converter configured to absorb the regenerative power sufficient to maintain bus voltage of the first vehicle DC bus within maximum continuous bus ratings, anda second DC-DC power converter in communication with the second vehicle DC bus and the second energy storage device and configured to match and regulate voltage between the second energy storage device and the second vehicle DC bus, the second energy storage device in combination with the second DC-DC power converter configured to absorb the regenerative power sufficient to maintain bus voltage of the second vehicle DC bus within maximum continuous bus ratings. 15. The aircraft electrical system as defined in claim 1, wherein the one or more electrical distribution unit buses comprises a first vehicle direct current (DC) bus positioned in electrical communication with the plurality of flight control actuators, anda second vehicle DC bus positioned in electrical communication with the plurality of flight control actuators;wherein the one or more energy storage devices comprises: a first energy storage device comprising an ultracapacitor positioned in electrical communication with the first vehicle DC bus and configured to provide power to each of the plurality of flight control actuators and to receive and absorb excess electrical power regenerated by the plurality of control actuators and to provide supplemental power to the plurality of control actuators, anda second energy storage device comprising a battery positioned also in electrical communication with the first vehicle DC bus to redundantly provide power to each of the plurality of flight control actuators and to redundantly receive and absorb peak excess electrical power regenerated by the plurality of control actuators and to redundantly provide supplemental power to the plurality of control actuators,a second DC-DC power converter in communication with the second vehicle DC bus and the second energy storage device and configured to match and regulate voltage between the second energy storage device and the second vehicle DC bus, the second energy storage device in combination with the second DC-DC power converter configured to absorb the regenerative power sufficient to maintain bus voltage of the second vehicle DC bus within maximum continuous bus ratings,wherein the one or more power converters comprises: a first DC-DC power converter in communication with the first vehicle DC bus and the first and the second energy storage devices to match and regulate voltage between the first and second energy storage devices and the first vehicle DC bus, the first and second energy storage devices in combination with the first DC-DC power converter configured to absorb the regenerative power sufficient to maintain bus voltage of the first vehicle DC bus within maximum continuous bus ratings;wherein the bidirectional accumulator is a first bidirectional accumulator; andwherein the aircraft electrical system further includes a second bidirectional accumulator in electrical communication with the second plurality of flight control actuators through the second electrical distribution unit bus, and positioned and configured to absorb excess electrical power regenerated by the second plurality of flight control actuators and positioned and configured to provide supplemental power to the second plurality of flight control actuators to thereby satisfy transient power requirements, the second bidirectional accumulator comprising: a first energy storage device comprising an ultracapacitor positioned in electrical communication with the second vehicle DC bus and configured to provide power to each of the plurality of flight control actuators and to receive and absorb excess electrical power regenerated by the plurality of control actuators and to provide supplemental power to the plurality of control actuators, anda second energy storage device comprising a battery also positioned in electrical communication with the second vehicle DC bus to redundantly provide power to each of the plurality of flight control actuators and to redundantly receive and absorb peak excess electrical power regenerated by the plurality of control actuators and to redundantly provide supplemental power to the plurality of control actuators,a second DC-DC power converter in communication with the second vehicle DC bus and the first and second energy storage devices and configured to match and regulate voltage between the first and second energy storage devices and the second vehicle DC bus, the first and second energy storage devices in combination with the second DC-DC power converter configured to absorb the regenerative power sufficient to maintain bus voltage of the second vehicle DC bus within maximum continuous bus ratings. 16. A method of managing electrical power for an aircraft electrical system of an aircraft comprising an aircraft flight control system including a plurality of electrically powered flight control actuators each positioned to move one of a 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 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, the method comprising the step of: absorbing regenerative power produced by the plurality of flight control actuators each having an electric motor operably coupled thereto to move one of the plurality of aerodynamic control surfaces, the absorbing performed by the bidirectional electrical accumulator electrically coupled to the plurality of flight control actuators. 17. The method as defined in claim 16, wherein the step of absorbing regenerative power includes absorbing transient voltages beyond that capable of being absorbed under maximum continuous conditions by the aircraft electrical system without a regenerative absorption device coupled thereto. 18. The method as defined in claim 17, wherein the aircraft electrical system includes an engine driven generator or a fuel cell to provide continuous aircraft electrical power, and wherein the method further comprises the step of satisfying transient power requirements beyond that capable of being supplied under maximum continuous conditions by the engine driven generator or fuel cell, the satisfying transient power requirements performed by the bidirectional electrical accumulator. 19. The method as defined in claim 16, wherein the aircraft electrical system includes an engine driven generator, the method further comprising the steps of: providing average continuous power by the engine driven generator to thereby satisfy average continuous power requirements;providing supplemental power to the plurality of flight control actuators by the bidirectional electrical accumulator to thereby satisfy transient power requirements; andcharging the bidirectional electrical accumulator by the engine driven generator when not encountering the transient power requirements to thereby maintain the bidirectional electrical accumulator at a minimum power level. 20. The method as defined in claim 19, wherein the aircraft electrical system includes at least one aircraft flight control actuation system bus electrically coupled to the plurality of flight control actuators and to the bidirectional electrical accumulator, and wherein the electrical bidirectional accumulator comprises at least one energy storage device and a corresponding at least one bidirectional power controller electrically coupled with the at least one energy storage device and to the at least one aircraft flight control actuation system bus, the method further comprising the step of: managing voltage between the at least one energy storage device and the at least one aircraft flight control actuation system bus by the at least one bidirectional power controller. 21. The method as defined in claim 16, wherein the plurality of flight control actuators is a first plurality of flight control actuators;wherein the bidirectional electrical accumulator includes: a first energy storage device electrically coupled to the first plurality of flight control actuators and redundantly coupled to a second plurality of flight control actuators, anda second energy storage device electrically coupled to the second plurality of flight control actuators and redundantly coupled to the first plurality of flight control actuators;wherein the step of absorbing regenerative power includes the first energy storage device absorbing excess electrical power regenerated by the first plurality of flight control actuators, and absorbing excess electrical power regenerated by the second plurality of flight control actuators when not sufficiently absorbed by the second energy storage device;wherein the method further comprises the steps of: the second energy storage device absorbing excess electrical power regenerated by the second plurality of flight control actuators and excess electrical power regenerated by the first plurality of flight control actuators when not sufficiently absorbed by the first energy storage device,the first energy storage device providing supplemental power to the first plurality of flight control actuators, and supplemental power to the second plurality of flight control actuators when not sufficiently provided by the second energy storage device, andthe second energy storage device providing supplemental power to the second plurality of flight control actuators, and supplemental power to the first plurality of flight control actuators when not sufficiently provided by the first energy storage device. 22. The method as defined in claim 16, wherein the plurality of flight control actuators is a first plurality of flight control actuators;wherein the aircraft electrical system includes: an engine driven generator,a first aircraft flight control actuation system bus electrically coupled to the first plurality of flight control actuators, anda second aircraft flight control actuation system bus electrically coupled to a second plurality of flight control actuators;wherein the electrical bidirectional accumulator further comprises: a first energy storage device positioned to absorb excess electrical power regenerated by the first plurality of flight control actuators and to provide supplemental power to the first plurality of flight control actuators,a second energy storage device positioned to absorb excess electrical power regenerated by the second plurality of flight control actuators and to provide supplemental power to the second plurality of flight control actuators,a first bidirectional power controller electrically coupled to the first energy storage device and the first aircraft flight control actuation system bus, anda second bidirectional power controller electrically coupled to the second energy storage device and the second aircraft flight control actuation system bus; andwherein the method further comprises the steps of: managing voltage between the first energy storage device and the first aircraft flight control actuation system bus by the first bidirectional power controller, andmanaging voltage between the second energy storage device and the second aircraft flight control actuation system bus by the second bidirectional power controller. 23. The method as defined in claim 22, further comprising the steps of: providing average continuous power to the plurality of flight control actuators by the engine driven generator to thereby satisfy average continuous power requirements by the engine driven generator;providing supplemental power to the first plurality of flight control actuators by the first energy storage device to thereby satisfy transient power requirements thereof;providing supplemental power to the second plurality of flight control actuators by the second energy storage device to thereby satisfy transient power requirements thereof;charging the first energy storage device by the engine driven generator when not encountering the transient power requirements to thereby maintain the bidirectional electrical accumulator at a minimum power level; andcharging the second energy storage device by the engine driven generator when not encountering the transient power requirements to thereby maintain the bidirectional electrical accumulator at a minimum power level. 24. The vehicle electrical system as defined in claim 23, wherein the first energy storage device comprises a capacitor having a minimum rating of 25 kilowatts, and wherein the second energy storage device comprises a battery having a minimum rating of 2.5 amp-hours.