Exterior aircraft light unit and aircraft comprising the same

• US 10,750,589 B2
• Filed: 10/23/2018
• Issued: 08/18/2020
• Est. Priority Date: 10/23/2017
• Status: Active Grant

• Current Assignee: Goodrich Lighting Systems GmbH (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Goodrich Lighting Systems GmbH (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Spinivasamurthy, Ramesh, Hessling-Von Heimendahl, Andre, Trinschek, Robert
• Primary Examiner(s): Johnson, Amy Cohen
• Assistant Examiner(s): Sathiraju, Srinivas
• Application Number:
  US16/167,632
• Publication Number:
  US 20190124739A1
• Time in Patent Office: 665 Days
• Field of Search: None
• CPC Class Codes: B64D 47/02 Arrangements or adaptations of signal or lighting devices
• CPC Class Codes: B64D 47/04 the lighting devices being primarily intended to illuminate the way ahead
• CPC Class Codes: B64D 47/06 for indicating aircraft presence
• CPC Class Codes: F21W 2107/30 for aircraft
• CPC Class Codes: H02H 3/085 making use of a thermal sensor, e.g. thermistor, heated by the excess current also responsive to the temperature of the protected device H02H5/041, thermal images H02H6/00
• CPC Class Codes: H02H 5/04 responsive to abnormal temperature specially adapted for electric machines H02H7/0852
• CPC Class Codes: H02H 9/02 responsive to excess current current limitation for voltage regulators G05F1/573; disconnection after limiting H02H3/025
• CPC Class Codes: H05B 45/14 using electrical feedback from LEDs or from LED modules
• CPC Class Codes: H05B 45/30 Driver circuits

Abstract

An exterior aircraft light unit includes at least two light sources. Each light source is provided with a variable current bypass component. Each variable current bypass component is configured to allow bypassing an adjustable electric current by the respective light source.

Claims

1. An exterior aircraft light unit comprising:

at least two light sources;

at least two temperature detectors; and

at least one control unit,

wherein each light source is provided with a variable current bypass component which is configured to allow bypassing an adjustable electric current by the respective light source,

wherein one of the temperature detectors is associated with each of the light sources, respectively, and configured for detecting the temperature of the respectively associated light source and for providing a corresponding temperature indicating signal;

wherein the at least one control unit comprises a comparison unit, which is configured for comparing the temperature indicating signals which each other and determining the light source having the lowest temperature, which is set as a reference temperature; and

wherein the at least one control unit is configured for controlling the variable current bypass components based on the temperature indicating signals provided by the temperature detectors so that the temperature of each light source does not deviate more than 10% from said reference temperature.

2. The exterior aircraft light unit according to claim 1, wherein the at least one control unit is configured for controlling the variable current bypass components in order to operate all light sources so that the temperature of each light source does not deviate more than 5% from a reference temperature.

3. The exterior aircraft light unit according to claim 1, wherein the control unit is configured for controlling the variable current bypass components of the light sources so that the respective temperatures of the light sources do not exceed a predetermined maximum temperature.

4. The exterior aircraft light unit according to claim 3, further comprising an adjustable power supply which is configured for supplying electrical power to the at least two light sources, wherein the at least one control unit is configured for controlling the adjustable power supply based on the temperature indicating signals.

5. The exterior aircraft light unit according to claim 1, wherein the temperature detectors are temperature sensitive elements or include temperature sensitive elements, which are configured for directly detecting the temperature of the respective light source, and

wherein the temperature detectors are temperature determination elements or include temperature determination elements, which are configured for determining the temperature of the respective light source indirectly from at least one other detected or measured parameter, wherein said parameter in particular includes the flux generated by the respective light source.

6. The exterior aircraft light unit according to claim 1, wherein the at least two light sources are serially connected to a common power supply.

7. The exterior aircraft light unit according to claim 1, wherein the light sources are LEDs or comprise LEDs.

8. The exterior aircraft light unit according to claim 1, wherein each variable current bypass component includes at least one transistor or at least one adjustable resistor.

9. The exterior aircraft light unit according to claim 1, wherein the exterior aircraft light unit is configured to be employed as at least one of a navigation light, a taxi light, a landing light, a takeoff light, and a runway turn-off light, a cargo loading light, an anti-collision strobe light, an anti-collision beacon light, a logo light, a wing scan light, or an engine scan light.

10. An aircraft comprising at least one exterior aircraft light unit according to claim 1.

11. A method of operating an exterior aircraft light unit comprising at least two light sources, each light source being provided with at least one variable current bypass component, which allows bypassing an adjustable current by the respective light source;

wherein the method includes;

detecting the temperature of each light source;

comparing the detected temperatures with each other and determining the lowest detected temperature;

setting the lowest detected temperature as a reference temperature; and

controlling the variable current bypass components so that the temperature of each light source does not deviate more than 10% from the reference temperature.

12. The method according to claim 11, wherein the variable current bypass components is controlled so that the temperature of each light source does not deviate more than 5% from the reference temperature.