ELECTRIC ACCUMULATOR UTILIZING AN ULTRA-CAPACITOR ARRAY

• US 20120280564A1
• Filed: 07/16/2012
• Published: 11/08/2012
• Est. Priority Date: 12/15/2009
• Status: Active Grant

• Current Assignee: Safran Landing Systems Canada Incorporated / Safran Systemes D'Atterrissage Canada Incorporated
• Original Assignee: Messier-Dowty Incorporated (Safran SA)
• Inventors: BROOKFIELD, Chris
• Granted Patent: US 10,432,016 B2
• Time in Patent Office: Days
• US Class Current: 307/9.1
• CPC Class Codes: H02J 2310/44 for aircrafts
• CPC Class Codes: H02J 7/345 using capacitors as storage or buffering devices
• CPC Class Codes: H02J 9/061 for DC powered loads

Abstract

Disclosed is an electric accumulator for selectively operating at least one aircraft device. The electric accumulator includes an ultra-capacitor array for storing electrical energy, which can later be used to power an aircraft device. The stored electrical energy can also be used as a source of emergency backup power. The distribution of the electrical energy is controlled by a power distribution controller. The electric accumulator may be charged by a power source on an aircraft, or it may be pre-charged by an external power source.

Claims

1. An electric accumulator for selectively operating an aircraft device, comprising:

an ultra-capacitor for storing electrical energy from a power source;

an output connector configured to selectively couple the ultra-capacitor to the aircraft device; and

a power distribution controller operatively connected to the output connector for controlling flow of electrical energy from the ultra-capacitor, the power distribution controller configured to;

selectively close the output connector to power the aircraft device using the electrical energy from the ultra-capacitor by allowing it to flow to the aircraft device.

2. The electric accumulator of claim 1, wherein the output connector is configured to couple both the ultra-capacitor and the power source to the aircraft device.

3. The electric accumulator of claim 2, wherein the power distribution controller is further configured to selectively close the output connector to power the aircraft device using the electrical energy from both the ultra-capacitor and the power source.

4. The electric accumulator of claim 1, further comprising an input connector configured to selectively couple the ultra-capacitor to a power source, the power distribution controller is operatively connected to the input connector for controlling flow of electrical energy to the ultra-capacitor,

the power distribution controller is further configured to:

determine power demand on the power source;

selectively close the input connector to charge the ultra-capacitor by allowing electrical energy to flow into the ultra-capacitor if the power demand is low; and

selectively open the input connector to restrict electrical energy from flowing into the ultra-capacitor if the power demand is high.

5. The electric accumulator of claim 1, further comprising at least one additional ultra-capacitor for storing electrical energy, the at least one additional ultra-capacitor arrayed in series with the ultra-capacitor for increasing voltage of the electric accumulator.

6. The electric accumulator of claim 1, further comprising at least one additional ultra-capacitor for storing electrical energy, the at least one additional ultra-capacitor arrayed in parallel with the ultra-capacitor for increasing power output of the electric accumulator.

7. The electric accumulator of claim 1, wherein the aircraft device is an electrical or electro-mechanical load device which is at least partially operable by electrical energy.

8. The electric accumulator of claim 1, further comprising a second aircraft device, the second aircraft device coupled to the output connector, the ultra-capacitor providing stored electrical energy to the second aircraft device for powering the second aircraft device.

9. The electric accumulator of claim 1 wherein the power source is an aircraft electrical supply.

10. The electric accumulator of claim 1 wherein the power source is an external power supply.

11. The electric accumulator of claim 1 wherein the aircraft device receives all of its required power from the output connector of the ultra-capacitor.

12. The electric accumulator of claim 1, further comprising a diode operatively connected to the ultra-capacitor, the diode for restricting electric current from flowing from the ultra-capacitor to the power source.

13. The electric accumulator of claim 12, further comprising a second diode operatively connected to the ultra-capacitor, the second diode for restricting electric current from flowing to the ultra-capacitor from the output connection.

14. The electric accumulator of claim 12, the power distribution controller for selectively allowing electrical energy to flow back into the power source.

15. An electric accumulator for selectively operating an aircraft device, comprising:

an ultra-capacitor for storing electrical energy, the ultra-capacitor configured to power the aircraft device from both the ultra-capacitor and the power supply.

16. The electric accumulator of claim 15 wherein the ultra-capacitor having an output connector to couple both the ultra-capacitor and the power supply to the aircraft device.

17. A method of providing power to an aircraft device using an ultra-capacitor, the method comprising the steps of:

coupling the ultra-capacitor to a power source;

directing power from the power source to the ultra-capacitor for storing electrical energy; and

selectively coupling the ultra-capacitor to the aircraft device to provide the electrical energy to the aircraft device.

18. The method of claim 17, wherein selectively coupling includes coupling the ultra-capacitor to the aircraft device and the power source.

19. The method of claim 17, further comprising:

determining power demand on the power source; and

selectively coupling an input connector of the ultra-capacitor based on the power demand to charge and discharge the ultra-capacitor.

20. The method of claim 19, wherein selectively coupling the input connector further includes closing the input connector to charge the ultra-capacitor by when the power demand is low and opening the input connector to restrict electrical energy from flowing into the ultra-capacitor if the power demand is high.