Multi-platform LED-based aircraft rear position light

• US 7,434,970 B2
• Filed: 08/18/2004
• Issued: 10/14/2008
• Est. Priority Date: 03/12/2004
• Status: Expired due to Fees

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Singer, Jeffrey M., Machi, Nicolo F., McKenzie, Mark A.
• Primary Examiner(s): Sawhney; Hargobind S
• Application Number:
  US10/920,524
• Publication Number:
  US 20050201112A1
• Time in Patent Office: 1,518 Days
• Field of Search: 362/470, 362473-475, 362477-479, 362/486, 362/493, 362538-540, 362542-548, 362/549, 362/294, 362/373, 362/800, 362/487, 362/507, 340/953, 340/981, 340/982, 340/815.45, 340/815.73, 340/815.75, 340/815.76
• US Class Current: 362/470
• 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: F21V 29/70 characterised by passive heat-dissipating elements, e.g. heat-sinks
• CPC Class Codes: F21V 5/046 the lens having a rotationally symmetrical shape about an axis for transmitting light in a direction mainly perpendicular to this axis, e.g. ring or annular lens with light source disposed inside the ring
• CPC Class Codes: F21V 7/0091 using total internal reflection
• CPC Class Codes: F21W 2107/30 for aircraft
• CPC Class Codes: F21Y 2115/10 Light-emitting diodes [LED]

Abstract

An aircraft rear position light device (1) has a modular configuration. The device utilizes solid-state light sources. In an exemplary embodiment, the light sources are side-emitting light-emitting diodes (LEDs) (40), which are attached to a heat sink (30). A reflector (200) is positioned next to each of the LEDs. The device further includes an outer lens (10) with an integrated cut-off shield (110) and optical treatments (120). The configuration of LEDs and reflectors, in conjunction with the cut-off shield and optical treatments, allows the emitted light to satisfy predetermined minimum and maximum angular intensity requirements. An electronics module (50) is also attached to the heat sink to connect the LEDs to a power source in the aircraft. Electronic updates may be made by replacing the electronics module.

Claims

1. A rear position lighting device configured to be mounted at a rear position light mounting platform of an aircraft, the rear position light mounting platform corresponding to a tail or wing of the aircraft, the device comprising:

a heat sink;

a plurality of solid-state light sources operably connected to the heat sink;

an outer lens through which light from the solid-state light sources is emitted;

a cut-off shield operably attached to the outer lens, the cut-off shield being configured to limit the light transmitted through the outer lens according to angular cut-off parameters;

at least two reflectors, each corresponding to one of the solid-state light sources for redirecting the light emitted by the solid-state light sources toward an area of the outer lens exposed by the cut-off shield, wherein each reflector is configured to redirect light from sides of an emitter in the corresponding solid-state light source, so that the redirected light is transmitted through the outer lens;

wherein the redirected light from each reflector is directed by the cut-off shield according to the angular cut-off parameters

at least two fastening modules, each configured to fasten one of the solid-state light sources to the heat sink, wherein each of the reflectors is attached to a corresponding one of the fastening modules;

wherein during operation, the device is mounted to the rear position light mounting platform of the aircraft, and

the device is dimensioned to be mountable at the rear position light mounting platforms of multiple types of aircraft, without modifying the corresponding tail or wing, in such a manner that the device fits within the corresponding tail or wing when mounted.

2. The device of claim 1, wherein the solid-state light sources are light-emitting diodes (LEDs) configured to emit a white light.

3. The device of claim 2, wherein at least two of the LEDs are side-emitting LEDs, each side-emitting LED emitting a light around an optical axis incident to a mounting surface of the side-emitting LED such that radiant intensity of the side-emitting LED peaks in the range of 60-100 degrees off the optical axis.

4. The device of claim 3,

wherein each of the side-emitting LEDs is oriented such that an emitter in the side-emitting LED emits light from the emitter'"'"'s sides through the outer lens.

5. The device of claim 4, wherein the outer lens includes optical treatments.

6. The device of claim 1, wherein dimensions of the heat sink and the outer lens are compatible with the rear position light mounting platforms of multiple types of aircraft, thereby allowing the device to be mounted to the rear position light mounting platform without retrofitting the device or modifying the corresponding tail or wing.

7. The device of claim 1, wherein a casting of the heat sink comprises cooling fins incorporated in the casting of the heat sink module.

8. A rear position lighting device for an aircraft, which is configured to emit light satisfying a minimum intensity within an angular range, the device comprising:

a heat sink;

two side-emitting LEDs operably connected to the heat sink, each having an emitter configured so that light is emitted from the emittert'"'"'s sides within the angular range; and

a cut-off shield configure to limit the reflected light from the two reflectors according to the angular range, and

two reflectors, each corresponding to one of side-emitting LEDs each reflector being configured to reflect light from the sides of the emitter in the corresponding side-emitting LED, so that the reflected light is transmitted within the angular range,

wherein each side-emitting LED emits a light around an optical axis incident to a mounting surface of the side-emitting LED such that radiant intensity of the side-emitting LED peaks in the range of 60-100 degrees off the optical axis; and

wherein the device is mounted at the rear position light mounting platform of the aircraft.

9. The device of claim 8, further comprising:

two fastening modules, each fastening module being configured to clamp one of the side-emitting LEDs against the heat sink,

wherein each of the reflectors is operably attached to a corresponding one of the fastening modules.

10. The device of claim 8, further comprising

a cut-off shield configured to limit the emitted light of the device according to angular cut-off parameters.

11. The device of claim 10, wherein the angular cut-off parameters is configured to limit overlapping between the emitted light and forward position lights of the aircraft.

12. The device of claim 10, wherein the cut-off shield is operably attached to an outer lens of the device.

13. The device of claim 12, wherein the outer lens is operably attached to the heat sink, and

the dimensions of the outer lens and heat sink are compatible with each of a plurality of distinct mounting platforms, thereby allowing the device to be mounted to the distinct mounting platform without retrofitting the device or modifying the mounting platform.

14. The device of claim 8, wherein a shape of each reflector is determined based on light-emitting characteristics of the corresponding side-emitting LED.

15. The device of claim 14, wherein each of the reflectors include a curved reflective surface, which is substantially concave with respect to the aft of the aircraft.

16. The device of claim 8, further comprising:

an interchangeable electronics module operably attached to the heat sink, the electronics module including electronic circuitry for electrically connecting the side-emitting LEDs to a power source within the aircraft, the electronics module being interchangeable with another electronics module having different electronic circuitry.

17. The device of claim 8, wherein a casting of the heat sink incorporates cooling fins.

18. A rear position lighting device for an aircraft, which is configured to emit light satisfying a minimum intensity within an angular range, the device comprising:

a heat sink;

two side-emitting LEDs operably connected to the heat sink, each having an emitter configured so that light is emitted from the emitter'"'"'s sides within the angular range; and

two reflectors, each corresponding to one of side-emitting LEDs, each reflector being configured to reflect light from the sides of the emitter in the corresponding side-emitting LED, so that the reflected light is transmitted within the angular range, and a cut-off shield configure to limit the reflected light from the two reflectors according to the angular range, wherein the device is mounted at the rear position light mounting platform of the aircraft,

wherein maximum light intensity from each side-emitting LED is emitted from the sides of the corresponding emitter, such that primary source of light emitted by the device is a combination of the light emitted from the sides of the emitters and the light reflected by the reflectors.