Solid state tail light for aircraft

Details Solid state tail light for aircraft Solid state tail light for aircraft

1998-10-05

2001-02-20

Wong, Don (Department: 2821)

Electric lamp and discharge devices: systems

Current and/or voltage regulation

Automatic regulation

C315S077000, C362S296040

Reexamination Certificate

active

06191541

ABSTRACT:

FIELD OF THE INVENTION
The present invention relates generally to a light for an aircraft or other application where the light is subjected to temperature changes and vibration.
BACKGROUND OF THE INVENTION
Aircraft use various external lights in order to provide functional illumination as well as positional indication. For example, the front lights of an aircraft are used primarily for illumination purposes while the lights on the wing tips and the tail are used primarily to indicate the location of the various aircraft components. Such external lights, for example, the tail light, experience substantial vibrational loading during aircraft operation. This causes a substantially high failure rate in prior art external lights employing incandescent type bulbs due to the fragility of the filament. Consequently, the external tail light is typically replaced about every ten (10) days. This periodic replacement of the external light is expensive both in terms of the replacement bulb cost and the labor cost associated with the bulb replacement. Therefore there is a need in the art for a more reliable external light for aircraft.
SUMMARY OF THE INVENTION
The present invention relates to a light and associated method having particular use with an aircraft. The light includes a solid state illumination device, for example, one or more light emitting diodes (LEDs), and a thermal compensator which maintains the temperature of the illumination device above a minimum threshold or in accordance with some other temperature criteria. A substantial improvement in reliability over prior art incandescent bulbs having fragile filaments arises from the use of the solid state illumination device because the solid state illumination device is substantially rugged and performs well in environments experiencing high vibrational loading, thus substantially reducing the replacement and maintenance costs for the external light. On the other hand, desired performance under changing temperature conditions is assured by the thermal compensator.
More particularly, the light and associated method provide illumination over a broad temperature range by providing thermal compensation for the solid state illumination device. When the light is subjected to low temperatures, such as when the aircraft is at high altitudes, the thermal compensator provides compensation to maintain the illumination device above a predetermined threshold temperature above which the solid state illumination device may efficiently operate.
According to another aspect of the present invention, a vehicle light includes a solid state illumination device which contains a plurality of discrete illumination elements. Each of the elements have an illumination axis and at least one of the elements has such an axis which is not parallel with some of the other illumination elements for providing a desired illumination pattern. Consequently, the solid state illumination device may be configured in a variety of ways to provide a customized illumination pattern.
According to still another aspect of the present invention, a light unit includes a housing having a solid state illumination device carried thereby. The housing has an optical window that allows light from the illumination device to pass therethrough. The light unit also includes a heater which is carried by the housing, which heater maintains a temperature of the illumination device above a temperature threshold, within a prescribed temperature or performance range, etc.
Although the present invention was conceived and developed for an external aircraft light and is described chiefly in this context, the principles of the invention in their broader aspects can be adapted to nonaircraft lighting systems where substantial vibrational loading make conventional incandescent bulbs unreliable and where the system experiences substantial fluctuations in the thermal environment. The present invention contemplates such other applications.
To the accomplishment of the foregoing and related ends, the invention comprises the features hereinafter fully described and particularly pointed out in the claims. The following description and the annexed drawings set forth in detail certain illustrative embodiments of the invention. These embodiments are indicative, however, of but a few of the various ways in which the principles of the invention may be employed. Other objects, advantages and novel features of the invention will become apparent from the following detailed description of the invention when considered in conjunction with the drawings.


REFERENCES:
patent: 4233652 (1980-11-01), Oswald
patent: 4597033 (1986-06-01), Meggs et al.
patent: 5040022 (1991-08-01), Kinoshita et al.
patent: 5184114 (1993-02-01), Brown
patent: 5406172 (1995-04-01), Bennett
patent: 5600206 (1997-02-01), Cashin
patent: 5661645 (1997-08-01), Hochstein
patent: 5767934 (1998-06-01), Goddard
patent: 5783909 (1998-07-01), Hochstein
patent: 5838247 (1998-11-01), Bladowski
patent: 5929568 (1999-07-01), Eggers
patent: 5984494 (1999-11-01), Chapman et al.

Affiliated with

Also associated with

Rating

Solid state tail light for aircraft does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Solid state tail light for aircraft, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Solid state tail light for aircraft will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-2596990