White anti-collision light utilizing light-emitting diode (LED) technology

• US 7,414,546 B2
• Filed: 04/19/2005
• Issued: 08/19/2008
• Est. Priority Date: 07/08/2004
• Status: Expired due to Fees

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Singer, Jeffrey M., Lundberg, John L.
• Primary Examiner(s): Bugg; George A
• Assistant Examiner(s): LAU, HOI CHING
• Application Number:
  US11/109,439
• Publication Number:
  US 20060007013A1
• Time in Patent Office: 1,218 Days
• Field of Search: 340971-983, 340/815.45, 315/185.R, 315/165.R, 362/327, 362/470
• US Class Current: 340/961
• CPC Class Codes: B64D 2203/00 Aircraft or airfield lights using LEDs
• CPC Class Codes: B64D 47/06 for indicating aircraft presence
• CPC Class Codes: F21W 2107/30 for aircraft
• CPC Class Codes: H05B 45/32 Pulse-control circuits
• CPC Class Codes: H05B 45/345 Current stabilisation; Maintaining constant current
• CPC Class Codes: H05B 45/36 Circuits for reducing or suppressing harmonics, ripples or electromagnetic interferences [EMI]
• CPC Class Codes: H05B 45/48 having LEDs organised in strings and incorporating parallel shunting devices
• CPC Class Codes: H05B 45/58 involving end of life detection of LEDs
• CPC Class Codes: H05B 47/17 Operational modes, e.g. switching from manual to automatic mode or prohibiting specific operations

Abstract

A white anti-collision light mounted on an aircraft utilizes a set of high-power light-emitting diodes (LEDs) and dedicated reflectors to distribute the light in a particular pattern that satisfies predetermined intensity requirements along a horizontal coverage area. The anti-collision light may include heat pipes for transferring heat from the LEDs to a set of cooling fins. Also, the LEDs may be electrically connected and controlled to provide redundancy and mitigate the effects of LED failures.

Claims

1. An aircraft anti-collision light, comprising:

a light module including

two mounting surfaces angularly displaced from one another,

a plurality of light-emitting diodes (LEDs) mounted onto each of the mounting surfaces, and

a reflector block mounted onto each of the mounting surfaces, wherein a plurality of reflectors are integrally formed into each reflector block such that each of the reflectors is dedicated to and surrounds a particular one of the LEDs; and

a housing operably connected to the light module, the housing being formed to be mounted to a wing or the aft of the aircraft,

wherein the light module is configured to emit a pattern of light that satisfies a predetermined intensity over a coverage area greater than 110 degrees along a horizontal plane, and

the peak intensity of light emitted by at least one of the plurality of LEDs is directed toward the corresponding reflector.

2. The anti-collision light of claim 1, wherein the contours of each of the reflectors is designed to redistribute the light from the corresponding LED so that the pattern of light satisfies the predetermined intensity in the coverage area.

3. The anti-collision light of claim 2, wherein

the angular positions of the mounting surfaces gives each of LEDs a predetermined orientation with respect to the light module, and

the orientations of the plurality of LEDs are designed in conjunction with the contours of the dedicated reflectors so that the pattern of light satisfies the predetermined intensity in the coverage area.

4. The anti-collision light of claim 2, wherein the contours of each of the reflectors is designed using computer-aided design (CAD) technology.

5. The anti-collision light of claim 1, further comprising cooling fins operably connected to the housing.

6. The anti-collision light of claim 5, further comprising one or more heat pipes configured to transfer heat from the mounting surfaces of the light module to the cooling fins.

7. The anti-collision light of claim 6, wherein the two mounting surfaces of the light module are part of at least one heat conducting mounting plate on which the plurality of LEDs are mounted, each of the mounting surfaces being operably connected to a corresponding one of the heat pipes to transfer heat from the mounting plate to the cooling fins.

8. The anti-collision light of claim 1, wherein the plurality of LEDs are grouped into strings of two or more LEDs electrically connected in series.

13. The anti-collision light of claim 1, wherein the plurality of LEDs are controlled to flash at a rate which may be adjusted based on at least one of photometric and thermal requirements.

14. The anti-collision light of claim 1, wherein the plurality of LEDs include at least one side-emitting LED and at least one lambertian LED.

15. The anti-collision light of claim 1, wherein the plurality of LEDs include aviation white LEDs.

16. The anti-collision light of claim 15, wherein

the plurality of LEDs further include infrared (IR) LEDs, and

the anti-collision light is switchable between the following operating modes:

a visible mode, and an IR mode.

17. A system comprising a plurality of the anti-collision lights of claim 15, wherein the plurality of the anti-collision lights are mounted on the same aircraft.

18. The system of claim 17, wherein the plurality of anti-collision lights satisfy the predetermined intensity 360 degrees along the horizontal plane.

21. The aircraft light of claim 1, wherein the at least one of the plurality of LEDs includes a side-emitting LED which emits light around its optical axis such that radiant intensity peaks in the range of 60-100 degrees off the optical axis.

9. An anti-collision light, comprising:

a light module including a plurality of light-emitting diodes (LEDs) and reflectors, each of the reflectors being dedicated to a particular one of the LEDs; and

a housing operably connected to the light module, the housing being formed to be mounted to a wing or the aft of the aircraft,

wherein

the light module is configured to emit a pattern of light that satisfies a predetermined intensity over a coverage area greater than 110 degrees along a horizontal plane,

the light emitted by at least one of the plurality of LEDs is substantially directed toward the corresponding reflector, and

the plurality of LEDs are grouped into strings of two or more LEDs electrically connected in series,

the anti-collision light further comprising monitor circuitry, which is configured to;

monitor the operating status of the LEDs in each of the strings, and

shut off the anti-collision light if a predetermined number of the LEDs in any of the strings fail.

10. The anti-collision light of claim 9, wherein

the plurality of LEDs are grouped into two strings, and

the monitor circuitry is configured to shut down the anti-collision light if two of the LEDs in any of the strings fail.

11. The anti-collision light of claim 9, wherein the monitor circuitry includes an LED sensing circuit for each string, which is configured to monitor potential voltage drops across the LEDs in the corresponding string.

12. The anti-collision light of claim 11, wherein the LED sensing circuit provides an alternative current path for the LEDs in the corresponding string in response to an LED failure.

19. An aircraft light, comprising:

a light module including

two mounting surfaces angularly displaced from one another,

a plurality of light-emitting diodes (LEDs) mounted onto each of the mounting surfaces, and

a reflector block mounted onto each of the mounting surfaces, wherein a plurality of reflectors are integrally formed into each reflector block such that each of the reflectors is dedicated to and surrounds a particular one of the LEDs;

a housing operably connected to the light module, the housing being formed to be mounted to a wing or the aft of the aircraft; and

heat pipes operably connecting each of the mounting surfaces, respectively, to the housing in order to transfer heat from the mounting surface to the housing,

wherein at least one of the plurality of LEDs is a side-emitting LED, such that the peak intensity of light emitted by the at least one of the plurality of LEDs is directed toward the corresponding reflector.

20. The aircraft light of claim 19, wherein

the aircraft light is configured to switchably operate in the following modes:

a flashing aft anti-collision light mode, and a non-flashing aft position light mode, and

current is supplied to the LEDs based on the mode in which the aircraft light is operating.

22. The aircraft light of claim 19, wherein the side-emitting LED which emits light around its optical axis such that radiant intensity peaks in the range of 60-100 degrees off the optical axis.