Recognition/anti-collision light for aircraft
First Claim
1. A recognition light for an aircraft, comprising:
- a flashtube;
a flash capacitor connect d to the flashtube;
a power regulator for changing the flash capacitor to a first voltage level prior to being discharged through the flashtube;
a light detector positioned to detect light emitted from the flashtube;
a monitor circuit connected to the light detector for measuring the intensity of the detected light, comparing the measured intensity with a reference value corresponding to a predetermined light intensity level, and outputting a signal when a specified relationship exists between the measured intensity and the reference value that indicates a need to increase the light intensity of the flashtube; and
a control circuit connected to the power regulator and monitor circuit which causes the power regulator, in response to said signal from the monitor circuit, to charge the flash capacitor to a second voltage level higher than said first voltage level prior to being discharged through the flashtube, whereby the flashtube initially operates at a first power level and then at a second higher power level.
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Accused Products
Abstract
A recognition light includes a reflector having an axis and first and second annular semi-parabolic reflective surfaces which have respective focal points axially spaced apart from one another, and first and second annular lamps respectively disposed at the focal points. A cover surrounds the reflector and lamps and includes a lens for focusing the light along a plane perpendicular to the axis of the reflector, the lens including first and second Fresnel lens portions each including a convex lens and a prism lens, the convex lenses being disposed adjacent one another and transaxially aligned with the first and second lamps, respectively. A light detector detects light emitted from at least one of the lamps, a monitor circuit provides a fail signal when a characteristic of the light output of at least one of the lamps does not satisfy a specified criteria, and a control circuit first activates the first lamp and then the second lamp in response to receipt of the fail signal of the monitor circuit.
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Citations
9 Claims
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1. A recognition light for an aircraft, comprising:
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a flashtube;
a flash capacitor connect d to the flashtube;
a power regulator for changing the flash capacitor to a first voltage level prior to being discharged through the flashtube;
a light detector positioned to detect light emitted from the flashtube;
a monitor circuit connected to the light detector for measuring the intensity of the detected light, comparing the measured intensity with a reference value corresponding to a predetermined light intensity level, and outputting a signal when a specified relationship exists between the measured intensity and the reference value that indicates a need to increase the light intensity of the flashtube; and
a control circuit connected to the power regulator and monitor circuit which causes the power regulator, in response to said signal from the monitor circuit, to charge the flash capacitor to a second voltage level higher than said first voltage level prior to being discharged through the flashtube, whereby the flashtube initially operates at a first power level and then at a second higher power level.
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2. A method for increasing the useful life of a recognition light of an aircraft, comprising:
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flashing a flashtube by repeatedly charging a flash capacitor to a first voltage and discharging the capacitor through the flashtube;
monitoring the light output of the flashtube;
comparing the measured light output of the flashtube with a reference value corresponding to a predetermined light intensity value;
increasing the voltage to which the flash capacitor is charged to a second voltage higher than the first voltage when a specified relationship exists between the measured light output and the reference value that indicates a need to increase the light intensity of the flashtube, thereby to increase the intensity of the flashes emitted by the flashtube.
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3. A method for increasing the useful life of a recognition light of an aircraft, comprising:
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flashing a flashtube;
monitoring the light output of the flashtube;
comparing the measured light output of the flashtube with a reference value corresponding to a predetermined light intensity value;
increasing the power delivered to the flashtube when a specified relationship exists between the measured light output and the reference value indicates a need to increase the light intensity of the flashtube, thereby to increase the intensity of the flashes emitted by the flashtube; and
providing a second flashtube operative to flash at a rate different than that of the first flashtube. - View Dependent Claims (4, 5)
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6. A method for monitoring the useful life of an aircraft recognition light, comprising:
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flashing a flashtube;
monitoring the light output of the flashtube with a light detector that converts the detected light output into an integrated output voltage corresponding to the light output of a plurality of flashes of the flashtube;
providing an intensity comparator for comparing the integrated output voltage to a comparator reference voltage;
comparing the integrated output voltage to the comparator reference voltage and, if the integrated output voltage is less than the comparator reference voltage, transmitting a NOGO condition signal, and, if the integrated output voltage is greater than the comparator reference voltage, transmitting a GO condition signal;
storing the condition signal in an intensity status latch;
providing an intensity integrator fail counter for monitoring the GO/NOGO condition signal of the intensity status latch for a predetermined number of consecutive decreases and transmitting a boost signal or fail signal in response thereto;
monitoring the GO/NOGO condition signal and, if the predetermined number of consecutive NOGO measurements is attained, transmitting a boost signal for initiating an increase in power corresponding to an increase in the light output of the first flashtube; and
providing a second flash tube operative to flash at a rate different than that of the first flashtube, and continuing monitoring the GO/NOGO condition signal of the intensity status latch and, if the predetermined number of NOGO measurements is attained, transmitting a fail signal for initiating operation of the second flashtube at a rate substantially similar to the rate of the first flashtube. - View Dependent Claims (7, 8)
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9. A recognition light for an aircraft, comprising first and second flashtubes;
- and circuitry for operating either one of the first and second flashtubes at a first power level and later for operating at least one of the flashtubes at a second higher power level when the light intensity of said one of the flashtubes falls below a specified level, and wherein at least one of the first and second flashtubes is flashed at a first rate when operated at the first power level and at a second flash rate when operated at the second higher power level.
Specification