Aircraft emergency lighting system

Patent metadata

Field	Value
Publication number	US-11273757-B2
Application number	US-202016826119-A
Country	US
Kind code	B2
Filing date	Mar 20, 2020
Priority date	Mar 20, 2020
Publication date	Mar 15, 2022
Grant date	Mar 15, 2022

Abstract

An aircraft emergency lighting system is disclosed. This emergency lighting system may include interior emergency lighting, interior ambient light sensors, exterior emergency lighting, and exterior ambient light sensors. The interior emergency lighting, the exterior emergency lighting, or both, may be controlled based upon an input of the interior ambient light condition (e.g., using an output from at least one of the interior ambient light sensors) and based upon an input from at least one of the exterior ambient light sensors.

First claim

What is claimed:

1. An aircraft emergency lighting system, comprising:
at least one interior emergency light;
at least one exterior emergency light;
an interior ambient light condition source selected from the group consisting of at least one interior ambient light sensor and an interior ambient light derivation module;
at least one exterior ambient light sensor;
an emergency power source operatively interconnected with each of said at least one interior emergency light and said at least one exterior emergency light; and
an emergency lighting system controller operatively interconnected with each of said interior ambient light condition source and said at least one exterior ambient light sensor, wherein said emergency lighting system controller is further operatively interconnected with said emergency power source, wherein an interior ambient light condition and an exterior ambient light condition are each available to said emergency lighting system controller to control an intensity level output from said at least one interior emergency light, to control an intensity level output from said at least one exterior emergency light, or both.

2. The aircraft emergency lighting system of claim 1 , wherein said interior ambient light derivation module is configured to determine said interior ambient light condition from a control signal to at least one interior light prior to an activation of said aircraft emergency lighting system.

3. The aircraft emergency lighting system of claim 1 , wherein said interior ambient light derivation module is configured to determine said interior ambient light condition from at least one of a control signal to an interior light other than an interior emergency light, an output from said at least one exterior ambient light sensor, or both.

4. The aircraft emergency lighting system of claim 1 , wherein said emergency lighting system controller is configured to use a sensed exterior ambient light condition from said at least one exterior ambient light sensor to control operation of said at least one interior emergency light.

5. The aircraft emergency lighting system of claim 1 , wherein for a sensed exterior ambient light condition from said at least one exterior ambient light sensor exceeding an exterior ambient light threshold and for an interior ambient light condition from said interior ambient light condition source being below an interior ambient light threshold, said emergency lighting system controller is configured to increase an intensity level of said at least one interior emergency light.

6. The aircraft emergency lighting system of claim 5 , wherein said emergency lighting system controller is configured to increase said intensity level of said at least one interior emergency light starting from a minimum interior emergency light level for said at least one interior emergency light or from a last known state of said at least one interior emergency light, whichever is of a higher intensity.

7. The aircraft emergency lighting system of claim 5 , wherein said emergency lighting system controller is configured to rapidly increase said intensity level of said at least one interior emergency light.

8. The aircraft emergency lighting system of claim 1 , wherein for a sensed exterior ambient light condition from said at least one exterior ambient light sensor exceeding an exterior ambient light threshold and for an interior ambient light condition from said interior ambient light condition source exceeding an interior ambient light threshold, said emergency lighting system controller is configured to initiate operation of said at least one interior emergency light at a maximum intensity.

9. The aircraft emergency lighting system of claim 8 , wherein said emergency lighting system controller is configured to operate said at least one exterior emergency light in one of an off condition or at a minimum intensity level when said sensed exterior ambient light condition from said at least one exterior ambient light sensor exceeds said exterior ambient light threshold.

10. The aircraft emergency lighting system of claim 1 , wherein for a sensed exterior ambient light condition from said at least one exterior ambient light sensor being below an exterior ambient light threshold, said emergency lighting system controller is configured to operate said at least one interior emergency light in a lower intensity state.

11. The aircraft emergency lighting system of claim 10 , wherein said at least one interior emergency light is initially activated at a first intensity level, and wherein said emergency lighting system controller is configured to progressively reduce said intensity level of said at least one interior emergency light.

12. The aircraft emergency lighting system of claim 10 , wherein said emergency lighting system controller is configured operate said at least one exterior emergency light at a maximum intensity level.

13. The aircraft emergency lighting system of claim 10 , wherein said emergency lighting system controller is configured to terminate operation of said at least one interior emergency light in a first condition.

14. The aircraft emergency lighting system of claim 13 , wherein said first condition is expiration of a programmed time after said emergency lighting system has been activated.

15. An aircraft comprising a beacon and the aircraft emergency lighting system of claim 1 , wherein said emergency lighting system controller is configured to activate said beacon after operation of said at least one interior emergency light has been terminated by said emergency lighting system controller.

16. A method of operating an aircraft emergency lighting system, comprising:
determining a light intensity of a cabin of an aircraft;
monitoring a light intensity of an exterior environment of said aircraft; and
controlling operation of at least one interior emergency light for said aircraft, of at least one exterior emergency light for said aircraft, or both, based upon at least one of said determining step and said monitoring step, wherein each of said determining step and said monitoring step are available to control an intensity level output from said at least one interior emergency light, to control an intensity level output from said at least one exterior emergency light, or both.

17. The method of claim 16 , wherein when said monitoring step is used to determine that an exterior ambient light condition exceeds an exterior ambient light threshold and when said determining step determines that an interior ambient light condition is below an interior ambient light threshold, said method further comprises:
increasing an intensity level of said at least one interior emergency light; and
operating said at least one exterior emergency light in one of an off condition or at a minimum intensity level.

18. The method of claim 16 , wherein when said monitoring step is used to determine that an exterior ambient light condition exceeds an exterior ambient light threshold and when said determining step determines that an interior ambient light condition exceeds an interior ambient light threshold, said method further comprises:
operating said at least one interior emergency light at a maximum intensity; and
operating said exterior emergency light in one of an off condition or at a minimum intensity level.

19. The method of claim 16 , wherein when said monitoring step is used to determine that an exterior ambient light condition is below an exterior ambient light threshold, said method comprises operating said at least

Assignees

• Be Aerospace Inc

Inventors

• Edquist John
• Fredrich Jeremy

Classifications

• B60Q3/47 Primary

  Circuits; Control arrangements · CPC title

• B64D2203/00

  Aircraft or airfield lights using LEDs · CPC title

• B60Q3/46

  Emergency lighting, e.g. for escape routes · CPC title

• B64D2011/0038

  Illumination systems for cabins as a whole · CPC title

• B64D2045/007

  Indicators or signs in the cabin, e.g. exit signs or seat numbering · CPC title