Fiber-optic lighting system

• US 5,647,658 A
• Filed: 05/11/1995
• Issued: 07/15/1997
• Est. Priority Date: 05/11/1995
• Status: Expired

• Current Assignee: Bouchaib Ziadi
• Original Assignee: Bouchaib Ziadi
• Inventors: Ziadi, Bouchaib
• Primary Examiner(s): Husar, Stephen F.
• Assistant Examiner(s): Sember, Thomas M.
• Application Number:
  US08/439,431
• Time in Patent Office: 796 Days
• Field of Search: 362/62, 362/32, 362/293, 362/373, 362/294, 362/307, 362/310, 362/311, 362/26, 362/330, 362/328, 362/20, 362/74, 362/75, 362/83.3
• US Class Current: 362/471
• CPC Class Codes: B60Q 3/43 General lighting
• CPC Class Codes: B60Q 3/44 Spotlighting, e.g. reading lamps
• CPC Class Codes: B60Q 3/46 Emergency lighting, e.g. for escape routes
• CPC Class Codes: B60Q 3/66 for distributing light among several lighting devices
• CPC Class Codes: B64D 11/00 Passenger or crew accommodation; Flight-deck installations not otherwise provided for
• CPC Class Codes: B64D 2011/0038 Illumination systems for cabins as a whole
• CPC Class Codes: B64D 2011/0053 Cabin passenger reading lights
• CPC Class Codes: G02B 6/0001 specially adapted for lighting devices or systems lighting or signalling on vehicles using light guides B60Q1/00; lighting devices for vehicle dashboards B60Q3/10; lighting devices for vehicle interior using light guides B60Q3/62; lighting devices mounted on the vehicle rear part using light guides F21S43/235; measuring arrangements having light conducting pointers G01D13/265; illumination of liquid crystal displays G02F1/1336; illuminated signs G09F13/00
• CPC Class Codes: G02B 6/0005 the light guides being of the fibre type G02B6/0003 takes precedence
• CPC Class Codes: G02B 6/353 the optical element being a shutter, baffle, beam dump or opaque element absorbers on light guide termination G02B6/243
• CPC Class Codes: G02B 6/3552 1x1 switch, e.g. on/off switch
• CPC Class Codes: G02B 6/3572 Magnetic force magnetic forces controlling reflecting elements in general G02B26/085; magneto-optic devices G02F1/09
• CPC Class Codes: G02B 6/3574 Mechanical force, e.g. pressure variations
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A fiber-optic lighting system is powered by a power supply connected to a high intensity light source which generates a beam of light. A first elongate light guide extends between a first end positioned within the beam of light and a second end positioned adjacent a lamp reflector. A second elongate light guide which is configured to emit light from a side also extends from a first end positioned within the beam of light. An elongate light fixture is positioned along the second light guide for directing light emitted from the side of the light guide.

Claims

1. A fiber-optic lighting system for lighting an interior of an aircraft, the interior having a wall, a floor and a ceiling, the lighting system comprising:

a power supply;

a high intensity light source connected to the power supply for generating a light beam and directing the beam along a path;

a first elongate light guide having first and second ends and a length extending between the first and second ends, the first end of the first light guide being positioned adjacent the light source and within the path of the light beam, the first light guide being configured to transmit light between the first and second ends of the first light guide;

a first lamp reflector connected to the second end of the first light guide for directing light transmitted to the second end of the first light guide into the aircraft interior;

a second elongate light guide having first and second ends and a length extending between the first and second ends, the first end of the second light guide being positioned adjacent the light source and within the path of the light beam, the second light guide having a side extending along the second light guide length, the second light guide being configured to emit light from the second light guide side as light is transmitted between the first and second ends of the second light guide; and

an elongate light fixture positioned along the second light guide length for directing light emitted from the side of the second light guide into the aircraft interior.

2. The lighting system of claim 1 further comprising:

a switch connected in series with the first light guide for selectively blocking the transmission of light from the light source to the first lamp reflector.

3. The lighting system of claim 1 further comprising:

a third elongate light guide having first and second ends and a length extending between the first and second ends, the first end being positioned adjacent the light source and within the path of the light beam, the third light guide being configured to transmit light between the first and second ends of the third light guide; and

a second lamp reflector connected adjacent the second end of the third light guide for directing light transmitted to the second end of the third light guide.

4. The lighting system of claim 3 further comprising:

a switch connected in series with the second light guide for selectively blocking the transmission of light from the light source to the second lamp reflector.

5. The lighting system of claim 1 further comprising:

a filter connected in series with at least one of the first and second light guides.

6. The light system of claim 5 wherein:

the filter is configured to inhibit the transmission of ultraviolet light.

7. The light system of claim 5 wherein:

the filter is configured to inhibit the transmission of infrared light.

8. A fiber-optic lighting system for lighting an interior of an aircraft, the interior having a wall, a floor and a ceiling, the lighting system comprising:

a power supply;

a high intensity light source connected to the power supply for generating a beam of light and directing the beam along a path;

an elongate light guide having first and second ends and a length extending between the first and second ends, the first end being positioned adjacent the light source and within the path of the light beam, the light guide having a side extending along the length, the light guide being configured to emit light from at least a portion of the side as light is transmitted between the first and second ends;

a lamp reflector connected to the second end of the light guide for directing light transmitted to the second end into the aircraft interior; and

an elongate light fixture positioned along the side of the light guide for directing light emitted from the portion of the light guide side into the aircraft interior.

9. The lighting system of claim 8 further comprising:

a switch connected in series with the light guide for selectively blocking the transmission of light to the lamp reflector without interfering with the transmission of light to the elongate light fixture.

10. The lighting system of claim 8 further comprising:

a second elongate light guide having first and second ends and a length extending between the first and second ends, the first end being positioned adjacent the light source and within the path of the light beam, the second light guide being configured to transmit light between the first and second ends of the second light guide; and

a second lamp reflector connected adjacent the second end of the second light guide for directing light transmitted to the second end of the second light guide.

11. The lighting system of claim 8 further comprising:

a filter connected in series with the light guide.

12. The light system of claim 11 wherein:

the filter is configured to inhibit the transmission of ultraviolet light.

13. The light system of claim 11 wherein:

the filter is configured to inhibit the transmission of infrared light.

14. An aircraft lighting system for lighting the interior of an aircraft, the interior having a wall, a floor and a ceiling, the system comprising:

a power supply;

a high intensity light source connected to the power supply for generating a beam of light and directing the beam along a path;

a first elongate light guide having first and second ends and a length extending between the first and second ends, the first end of the first light guide being positioned adjacent the light source and within the path of the light beam, the first light guide being configured to transmit light between the first and second ends of the first light guide;

a lamp reflector mounted within the interior of the aircraft and connected to the second end of the first light guide for directing light transmitted to the second end of the first light guide;

a second elongate light guide having first and second ends with a length extending between the first and second ends and a side extending along the length, the second light guide being positioned along one of the aircraft wall, floor and ceiling with the first end positioned within the path of the light beam generated by the light source, the second light guide being configured to emit light from the side as light is directed into the first end of the second light guide; and

an elongate light fixture positioned along the second light guide length.

15. The lighting system of claim 14 wherein:

the elongate light fixture is a reflective light fixture mounted adjacent one of the aircraft wall and ceiling, the fixture being configured to direct light emitted from the side of the second light guide toward one of the aircraft wall and ceiling for general aircraft lighting.

16. The lighting system of claim 14 wherein:

the elongate light fixture is an emergency light having a indicator strip mounted adjacent the aircraft floor, the fixture being configured to direct light emitted from the side of the second light guide toward the indicator strip to guide passengers toward an aircraft exit in an emergency.

17. The lighting system of claim 14 further comprising:

a third elongate light guide having first and second ends and a length extending between the first and second ends and a side extending along the length, the third light guide being positioned along one of the aircraft wall and ceiling with the first end positioned adjacent the light source and within the path of the light beam, the third light guide being configured to emit light from the side as light is directed into the first end of the third light guide; and

a second elongate light fixture positioned along the third light guide length, the second light fixture being a reflective light fixture mounted adjacent one of the aircraft wall and ceiling, the fixture being configured to direct light emitted from the side of the third light guide toward one of the aircraft wall and ceiling for general aircraft lighting.

18. The lighting system of claim 14 wherein:

the aircraft includes a plurality of seats attached to the aircraft floor; and

the lamp reflector is a reading lamp reflector positioned above one of the plurality of aircraft seats.

19. The lighting system of claim 14 wherein:

the aircraft includes a galley having a work surface; and

the lamp reflector is a flood lamp reflector positioned above the galley work surface.

20. The lighting system of claim 14 further comprising:

an indicator positioned adjacent the second end of the first light guide, the indicator being configured to be illuminated to signal passengers.

21. The lighting system of claim 20 wherein:

the indicator includes at least one indicium selected from a group of indicia comprising no-smoking, fasten-seat-belt and exit indicia.

22. The lighting system of claim 14 wherein:

the high intensity light source includes at least two lighting elements, each of the lighting elements providing a separate beam of light directed along a separate path; and

one of the first ends of the first and second light guides is positioned within the light beam path of one of the light elements, and the other of the first ends of the first and second light guides is positioned within the light beam path of the other of the light elements.

23. The lighting system of claim 14 further comprising:

an alternate high intensity light source connected to the power supply for providing a light beam directed along a path to the first ends of the first and second light guides upon failure of the first light source.

24. The lighting system of claim 14 further comprising:

a switch connected in series along the first light guide for selectively blocking the transmission of light to the lamp reflector.

25. The lighting system of claim 24 wherein:

the aircraft includes a plurality of seats attached to the aircraft floor; and

the lamp reflector is a reading lamp reflector positioned above one of the plurality of aircraft seats and the switch is operable by a person seated within the one aircraft seat.

26. The lighting system of claim 14 wherein:

the light guide includes shielding for inhibiting light transmission losses along the length of the guide.