ELECTRIC ACCUMULATOR UTILIZING AN ULTRA-CAPACITOR ARRAY

• US 20110140513A1
• Filed: 12/15/2009
• Published: 06/16/2011
• 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 8,242,624 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;

an input connector configured to couple the ultra-capacitor to a power source;

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

a power distribution controller operatively connected to the ultra-capacitor, the power distribution controller for allowing electrical energy to flow through the input connection into the ultra-capacitor.

2. 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 the voltage of the electric accumulator.

3. 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 the power output of the electric accumulator.

4. 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.

5. The electric accumulator of claim 1 wherein the aircraft device is selected from the group consisting of a landing gear device, an uplock, a landing gear actuator, a steering system and a braking system.

6. The electric accumulator of claim 1, further comprising at least one second aircraft device, the at least one second aircraft device connected to the ultra-capacitor, the ultra-capacitor providing stored electrical energy to the at least one second aircraft device for powering the aircraft device.

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

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

9. The electric accumulator of claim 1 wherein the aircraft device receives all of its required power from the electric accumulator.

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

11. The electric accumulator of claim 1 further comprising a second diode operatively connected to the ultra-capacitor, the second diode for blocking electric current from flowing into the output connection.

12. The electric accumulator of claim 10, the power distribution controller further operable to selectively allow electrical energy to flow back into the aircraft electrical supply.

13. A method of providing power to an aircraft device, comprising:

providing an electric accumulator as defined in claim 1;

coupling the electric accumulator to a power source;

directing power from the power source to the electric accumulator for storing in the ultra-capacitor of the electric accumulator;

coupling the electric accumulator to an aircraft device; and

directing power from the electric accumulator to the aircraft device to provide electrical energy to the aircraft device.

14. The method of claim 13 wherein the power supply is the aircraft electrical supply.

15. The method of claim 13 wherein the power supply is external to the aircraft and wherein the electric accumulator is selectively operatively connected only when the airplane is grounded.

16. The method of claim 13 wherein the aircraft device is an electrical or electro-mechanical load device which is at least partially operable by electrical energy.

17. The method of claim 13 wherein the aircraft device is selected from the group consisting of a landing gear device, an uplock, a landing gear actuator, a steering system and a braking system

18. The method of claim 13 wherein the power source is the aircraft electrical supply.

19. The method of claim 13 wherein the power source is an external power supply.

20. The method of claim 13 wherein the aircraft device receives all of its required power from the electric accumulator.