Exit door indication system

1. An aircraft emergency exit door indication system, comprising:

a first plurality of light sources;

a second plurality of light sources;

a controller in electronic communication with the first plurality of light sources and the second plurality of light sources;

a first sensor associated with a first exit door;

wherein the controller receives a first sensor feedback signal from the first sensor indicating an availability for egress through the first exit door;

the first plurality of light sources and the second plurality of light sources are is operated by the controller based upon the first sensor feedback signal to indicate a direction of egress with respect to the first exit door, wherein, in response to being operated by the controller;

the first plurality of light sources changes from emitting a first light comprising a first color to emitting a second light comprising a second color based upon the availability for egress through the first exit door; and

the second plurality of light sources is sequentially pulsed to provide a travelling light path towards at least one of the first exit door and a second exit door based upon the availability for egress through the first exit door.

2. The aircraft emergency exit door indication system of claim 1 , wherein the first plurality of light sources include at least one of a ceiling wash light, a sidewall wash light, a floor path light, a dome light, or a passenger service unit light; and

the second plurality of light sources include at least one of the ceiling wash light, the sidewall wash light, the floor path light, the dome light, or the passenger service unit light.

3. The aircraft emergency exit door indication system of claim 1 , further comprising:

a second sensor associated with the second exit door;

wherein the first plurality of light sources is logically separated from the second plurality of light sources based upon its location relative to the first exit door and the second exit door;

the controller receives a second sensor feedback signal from the second sensor indicating an availability for egress through the second exit door; and

the second plurality of light sources is operated by the controller based upon the second sensor feedback signal.

4. The aircraft emergency exit door indication system of claim 3 , wherein the second plurality of light sources is disposed along a longitudinal axis of an aisle for indicating a second direction of egress parallel to the longitudinal axis.

5. The aircraft emergency exit door indication system of claim 3 , further comprising:

a power supply; and

a power electronics configured to transmit an electric power from the power supply to at least one of the first plurality of light sources and the second plurality of light sources.

6. The aircraft emergency exit door indication system of claim 1 , wherein the first plurality of light sources is disposed along a longitudinal axis of an aisle for indicating a first direction of egress parallel to the longitudinal axis.

7. The aircraft emergency exit door indication system of claim 1 , wherein the first sensor comprises at least one of a temperature sensor, a pressure sensor, and a smoke sensor.

8. The aircraft emergency exit door indication system of claim 1 , wherein the first sensor is configured to detect at least one of a fire, a smoke, a congestion, a faulty latch, and a faulty inflatable.

9. An aircraft passenger compartment, comprising:

an aisle extending along a longitudinal axis;

a first exit door;

a first sensor associated with the first exit door;

a first plurality of light sources disposed along the longitudinal axis;

a second plurality of light sources disposed along the longitudinal axis;

a controller in electronic communication with the first plurality of light sources, the first sensor, and the second plurality of light sources;

wherein the controller receives a first sensor feedback signal from the first sensor indicating an availability for egress through the first exit door;

the first plurality of light sources and the second plurality of light sources are operated by the controller based upon the first sensor feedback signal to indicate a direction of egress with respect to the first exit door, wherein, in response to being operated by the controller;

the first plurality of light sources changes from emitting a first light comprising a first color to emitting a second light comprising a second color based upon the availability for egress through the first exit door; and

the second plurality of light sources is sequentially pulsed to provide a travelling light path towards at least one of the first exit door and a second exit door based upon the availability for egress through the first exit door.

10. The aircraft passenger compartment of claim 9 , wherein the first plurality of light sources include at least one of a ceiling wash light, a sidewall wash light, a floor path light, a dome light, or a passenger service unit light; and

the second plurality of light sources include at least one of the ceiling wash light, the sidewall wash light, the floor path light, the dome light, or the passenger service unit light.

11. The aircraft passenger compartment of claim 9 , further comprising:

a second exit door;

a second sensor associated with the second exit door;

wherein the controller is in electronic communication with the second sensor;

wherein the first plurality of light sources is logically separated from the second plurality of light sources based upon its location relative to the first exit door and the second exit door.

12. The aircraft passenger compartment of claim 11 , wherein the controller receives a second sensor feedback signal from the second sensor indicating an availability for egress through the second exit door.

13. The aircraft passenger compartment of claim 12 , wherein the second plurality of light sources is operated by the controller based upon the second sensor feedback signal.

14. The aircraft passenger compartment of claim 9 , further comprising:

a power supply; and

a power electronics configured to transmit an electric power from the power supply to the first plurality of light sources.

15. A method for operating an aircraft emergency exit door indication system, comprising:

receiving, by a controller, a first sensor feedback signal from a first sensor associated with a first exit door, wherein the first sensor feedback signal indicates an availability for egress through the first exit door; and

operating, by the controller, a first plurality of light sources and a second plurality of light sources based upon the first sensor feedback signal, wherein, in response to being operated by the controller:

the first plurality of light sources changes from emitting a first light comprising a first color to emitting a second light comprising a second color based upon the availability for egress through the first exit door; and

the second plurality of light sources is sequentially pulsed to provide a travelling light path towards at least one of the first exit door and a second exit door based upon the availability for egress through the first exit door.

16. The method of claim 15 , further comprising receiving, by the controller, a second sensor feedback signal from a second sensor associated with a second exit door.

17. The method of claim 16 , further comprising operating, by the controller, the second plurality of light sources based upon the second sensor feedback signal, wherein the first plurality of light sources is logically separated from the second plurality of light sources based upon its location relative to the first exit door and the second exit door.