Electric accumulator utilizing an ultra-capacitor array

Patent metadata

Field	Value
Publication number	US-10432016-B2
Application number	US-201213549838-A
Country	US
Kind code	B2
Filing date	Jul 16, 2012
Priority date	Dec 15, 2009
Publication date	Oct 1, 2019
Grant date	Oct 1, 2019

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.

First claim

What is claimed is:

1. An electric accumulator system for selectively operating a first aircraft device of a plurality of aircraft devices in an aircraft electrical system, the electric accumulator system comprising:
an ultra-capacitor configured to store electrical energy;
an input connector including a switch configured to selectively couple in electrical communication the ultra-capacitor to an aircraft power supply that is powered by an aircraft engine, the switch having a closed state, in which electrical energy is able to flow from the aircraft power supply to the ultra-capacitor, and an open state, in which electrical energy is prevented to flow from the aircraft power supply to the ultra-capacitor, thereby isolating the aircraft power supply from the electric accumulator system;
a first output connector configured to couple the ultra-capacitor to the first aircraft device;
a second output connector configured to couple the ultra-capacitor to a second aircraft device of the plurality of aircraft devices;
a sub-system controller operatively connected to the first aircraft device and to the second aircraft device, the sub-system controller configured to control distribution of the electrical energy from the ultra-capacitor to the first aircraft device and the second aircraft device, wherein the sub-system controller is configured to allow electrical energy to flow from the ultra-capacitor to one of the first and second aircraft devices, but not the other of the first and second aircraft devices, and vice versa; and
a power distribution controller operatively connected to the input connector, the first output connector and the second output connector for controlling flow of electrical energy to and from the ultra-capacitor, the power distribution controller configured to:
determine power demand on the power supply; and

(i) if the power demand on the aircraft power supply is high:
place the switch in the open state to prevent electrical energy from flowing into the ultra-capacitor from the aircraft power supply; and
use the sub-system controller to selectively close the first output connector to power the first aircraft device using the electrical energy from the ultra-capacitor, and to selectively open the second output connector to prevent the electrical energy from flowing to the second aircraft device; and

(ii) if the power demand on the aircraft power supply is low:
place the switch in the closed state to charge the ultra-capacitor by allowing electrical energy to flow into the ultra-capacitor from the aircraft power supply,

wherein the first aircraft device is selected from a group consisting of an electric landing gear steering system, an electric landing gear brake, or a landing gear actuator, and
wherein the ultra-capacitor is located on a landing gear of an aircraft or in a landing gear bay of the aircraft to improve performance of the electric accumulator system.

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

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

4. The electric accumulator system 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 system up to an aircraft electrical system voltage.

5. The electric accumulator system 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 system.

6. The electric accumulator system of claim 1 , wherein a third aircraft device of the plurality of aircraft devices is coupled to the first output connector, the ultra-capacitor providing stored electrical energy to the third aircraft device for powering the third aircraft device.

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

8. The electric accumulator system 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 aircraft power supply.

9. The electric accumulator system of claim 8 , 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 at least one of the first output connector or the second output connector.

10. The electric accumulator system of claim 8 , wherein the power distribution controller is configured for selectively allowing electrical energy to flow back into the aircraft electrical system.

11. A method of providing power to a first aircraft device of a plurality of aircraft devices in an aircraft electrical system using an ultra-capacitor, the method comprising the steps of:
locating the ultra-capacitor in a landing gear bay of an aircraft or on a landing gear of the aircraft;
coupling the ultra-capacitor by an input connector to an aircraft power supply that is powered by an aircraft engine, the input connector including a switch;
determining power demand on the aircraft power supply;
directing power from the aircraft power supply to the ultra-capacitor for storing electrical energy by closing the switch of the input connector;
coupling the ultra-capacitor to the first aircraft device using a first output connector;
coupling the ultra-capacitor to a second aircraft device of the plurality of aircraft devices using a second output connector;
coupling the ultra-capacitor to a sub-system controller that is configured to allow electrical energy to flow from the ultra-capacitor to one of the first and second aircraft devices, but not the other of the first and second aircraft devices, and vice versa; and
if the power demand on the aircraft power supply is high, independently controlling distribution of the electrical energy to the first aircraft device and the second aircraft device by:
preventing power from flowing into the ultra-capacitor from the aircraft power supply by opening the switch of the input connector;
selectively closing the first output connector to power the first aircraft device using the power from the ultra-capacitor; and
selectively opening the second output connector to prevent the power from flowing from the ultra-capacitor to the second aircraft device,
wherein the first aircraft device is selected from a group consisting of an electric landing gear steering system, an electric landing gear brake, or a landing gear actuator.

12. The method of claim 11 , wherein coupling the ultra-capacitor to the first aircraft device includes coupling both the ultra-capacitor and the aircraft power supply to the first aircraft device.

13. The method of claim 11 , wherein the method further comprises closing the switch to charge the ultra-capacitor if the power demand is low.

14. The method of claim 11 , further comprising restricting electric current from flowing from the ultra-capacitor to the power aircraft power supply.

15. The method of claim 11 , further comprising restricting

Assignees

• Brookfield Chris
• Safran Landing Systems Canada Inc

Inventors

• Brookfield Chris

Classifications

• H02J2105/32

  for aircrafts · CPC title

• H02J7/345

  using capacitors as storage or buffering devices · CPC title

• H02J9/061 Primary

  for DC powered loads · CPC title