Patent Description:
Aircraft are generally equipped with position lights. A position light system includes forward pointing lights mounted at each wingtip and a rear pointing white light (mounted on wingtips or tail). The lights are generally operated in continuous mode, and together provide visual information on aircraft position and heading through color identification to help reduce the risk of collision. <CIT> describes an aircraft with a multifunctional light unit for providing at least one of (i) directional signalling of the aircraft, (ii) status signalling of the aircraft, and (iii) identification signalling of the aircraft. It can be provided in addition to signalling lights, such as strobes on the outer edges or tips of the wings with flashing white light. The multifunctional light units may flash, indicating the direction of the aircraft. <CIT> describes aircraft wing tip lights. Other aircraft with lamps indicating the direction of travel are known from <CIT> and <CIT>.

An aircraft is disclosed, comprising a first pair of forward-facing flash position lamps disposed at a first wing tip, the first pair of flash position lamps comprising a first flash position lamp and a second flash position lamp, a second pair of forward-facing flash position lamps disposed at a second wing tip, the second pair of flash position lamps comprising a third flash position lamp and a fourth flash position lamp, and a controller in electronic communication with the first pair of flash position lamps, wherein at least one of the first flash position lamp and the second flash position lamp are configured to flash, while maintaining a combined intensity of the first pair of forward-facing flash position lamps above a desired intensity, to indicate a change in direction of the aircraft.

In this aircraft, and in the embodiments, each flash position lamp may be operated in a continuous mode and/or a flashing mode.

In various embodiments, the desired intensity in a line of flight of the aircraft is greater than <NUM> candela.

In various embodiments, the controller is configured to alternate power between the first flash position lamp and the second flash position lamp to indicate the change in direction of the aircraft.

In various embodiments, a first light output of the first flash position lamp is in the form of a first waveform comprising a first period and a first duty cycle, and a second light output of the second flash position lamp is in the form of a second waveform comprising a second period and a second duty cycle, wherein the first period is equal to the second period and the first duty cycle is less than the second duty cycle.

In various embodiments, the controller is configured to power the first flash position lamp in a continuous mode and the second flash position lamp in a flashing mode to indicate the change in direction of the aircraft.

In various embodiments, the aircraft further comprises a rear-facing flash position lamp, wherein the rear-facing flash position lamp is configured to flash to indicate the change in direction of the aircraft.

In various embodiments, the aircraft further comprises a sensor in electronic communication with the controller for control of the first pair of forward-facing flash position lamps, wherein controller detects the change in direction of the aircraft via the sensor and the controller controls the first pair of forward-facing flash position lamps in response to detecting the change in direction.

A method for signaling a change in direction for an aircraft is disclosed, comprising powering a first forward-facing flash position lamp disposed at a wing tip in a continuous ON mode before the change in direction, maintaining a second forward-facing flash position lamp disposed at the wing tip in a continuous OFF mode before the change in direction, and powering the second forward-facing flash position lamp disposed at the wing tip in a flashing mode in response to the change in direction.

In this method, and in the embodiments, each flash position lamp may be operated in a continuous mode and/or a flashing mode.

In various embodiments, the first forward-facing flash position lamp is powered at a constant output intensity, the constant output intensity is greater than a desired intensity.

In various embodiments, the second forward-facing flash position lamp is powered at an output intensity greater than the desired intensity.

The forgoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated herein otherwise and to the extent that they remain within the scope of the claims.

A more complete understanding of the present disclosure, however, may best be obtained by referring to the detailed description and claims when considered in connection with the following illustrative figures. In the following figures, like reference numbers refer to similar elements and steps throughout the figures.

The detailed description of exemplary embodiments herein makes reference to the accompanying drawings, which show exemplary embodiments by way of illustration. While these exemplary embodiments are described in sufficient detail to enable those skilled in the art to practice the disclosures, it should be understood that, within the scope of the claims, other embodiments may be realized and that logical changes and adaptations in design and construction may be made in accordance with this disclosure and the teachings herein.

The scope of the disclosure is defined by the appended claims and their legal equivalents rather than by merely the examples described. Also, any reference to tacked, attached, fixed, coupled, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option. Surface shading lines may be used throughout the figures to denote different parts but not necessarily to denote the same or different materials.

As used herein, the term "flash position lamp" refers to a position lamp which is capable of being flashed - i.e., flash-capable - and may be operated in a continuous mode and/or a flashing mode.

Disclosed herein is a flash position lamp system for signaling a change, or desired change, in direction of an aircraft. Flash position lamps may blink or flash to communicate an intended or actual direction change to other aircrafts and observers, therefore enhancing safety during flights and ground operations.

A flash position lamp system, as disclosed herein, may have particular application for ground operations (taxing). A flash position lamp system, as disclosed herein, may use two separate flash position lights on each side (most commercial aircrafts have two forward position lights on each side for redundancy). The flash position lamps may blink/flash so that there is always one light one on, therefore meeting the federal aviation regulation (FAR) requirement of continuous operation (as a pair). The rear-facing flash position lamp can also blink/flash and use a blink/flash pattern to indicate direction. From example, a blink for right turns and two successive blinks for left turns.

With reference to <FIG>, an aircraft <NUM> is provided with a plurality of flash position lamps for the purpose of aiding in identification and recognition of the aircraft while in flight, as well as aiding in identification and recognition of a direction of travel, or a change in the direction of travel, of the aircraft while in flight or on the ground. These flash position lamps may comprise the position lamps required by government regulations. These position lights may comprise red and green lamps on the left and right wing tips, respectively. These position lights may comprise a white lamp on the tail of the aircraft. A first pair of forward-facing flash position lamps <NUM>, <NUM> is mounted on a first wing tip <NUM> and a second pair of forward-facing flash position lamps <NUM>, <NUM> is mounted on a second wing tip <NUM>. A rear-facing flash position lamp <NUM> is mounted on the tail of the aircraft.

The forward-facing flash position lamps <NUM>, <NUM> and <NUM>, <NUM> are so mounted on the wing tips so that they may be seen by an observer positioned anywhere in the arc A shown in <FIG>. The rear-facing flash position lamp <NUM> is so mounted that they may be seen by an observer positioned anywhere in the arc B shown in <FIG>.

In various embodiments, forward-facing flash position lamps <NUM>, <NUM> may each emit a light comprising a first color, such as red for example. In various embodiments, forward-facing flash position lamps <NUM>, <NUM> may each emit a light comprising a second color, such as green for example. Rear-facing flash position lamp <NUM> may emit a light comprising a third color, such as white for example.

All the flash position lamps may be operated under the control of a controller <NUM>, shown in <FIG>. In this regard, flash position lamps <NUM>, <NUM>, <NUM>, <NUM>, <NUM> may be in electronic communication with controller <NUM> via one or more wires, or the like. Controller <NUM> may implement a timing circuit for providing individual input signals to each flash position lamp <NUM>, <NUM>, <NUM>, <NUM>, <NUM>. Controller <NUM> may control each flash position lamp <NUM>, <NUM>, <NUM>, <NUM>, <NUM> individually via separate power signals. In this regard, controller <NUM> may comprise five outputs, two of which are connected to flash position lamps <NUM>, <NUM> (also referred to herein as first and second flash position lamps), respectively, two of which are connected to flash position lamps <NUM>, <NUM> (also referred to herein as third and fourth flash position lamps), respectively, and one of which is connected to flash position lamp <NUM>. The outputs of controller <NUM> may take various forms as described herein.

Controller <NUM> may include one or more controllers (e.g., processors) and one or more tangible, non-transitory memories capable of implementing digital or programmatic logic. In various embodiments, for example, the one or more controllers are one or more of a general purpose processor, digital signal processor (DSP), application specific integrated circuit (ASIC), field programmable gate array (FPGA), or other programmable logic device, discrete gate, transistor logic, or discrete hardware components, or any various combinations thereof or the like.

System program instructions and/or controller instructions may be loaded onto a non-transitory, tangible computer-readable medium having instructions stored thereon that, in response to execution by a controller, cause the controller to perform various operations. The term "non-transitory" is to be understood to remove only propagating transitory signals per se from the claim scope and does not relinquish rights to all standard computer-readable media that are not only propagating transitory signals per se. Stated another way, the meaning of the term "non-transitory computer-readable medium" and "non-transitory computer-readable storage medium" should be construed to exclude only those types of transitory computer-readable media which were found in In Re Nuijten to fall outside the scope of patentable subject matter under <NUM> U.

The following description provides a method for controlling flash position lamps <NUM>, <NUM> in the context of a left-hand turn. Systems and methods are described primarily with respect to flash position lamps <NUM>, <NUM> during left-hand turns in order to reduce redundancy and improve overall clarity of the detailed description. It should be noted that control of flash position lamps <NUM>, <NUM> for a right-hand turn is similar to that of flash position lamps <NUM>, <NUM> for left-hand turns.

In various embodiments, controller <NUM> may detect the change, or desired change, in direction of travel via a switch <NUM> (e.g., located in the cockpit). For example, a pilot may actuate switch <NUM> to send a signal to controller <NUM> indicating a change in direction of travel of aircraft <NUM>. In various embodiments, controller <NUM> may automatically detect the change, or desired change, in direction of travel via a sensor <NUM> mounted on aircraft <NUM>. For example, controller <NUM> may monitor sensor <NUM> to detect a rotation about an axis of aircraft <NUM>. In various embodiments, sensor <NUM> is a yaw rate sensor for detecting an angular velocity around a vertical axis of aircraft <NUM>. Sensor <NUM> may be a gyroscopic device. Sensor <NUM> may be a piezoelectric sensor. Sensor <NUM> may be a micromechanical capacitive sensor.

In various embodiments, controller <NUM> may be mounted locally at wing tip <NUM>. In this manner, flash position lamps <NUM>, <NUM> and controller <NUM> may be retrofittable. It is contemplated that one or more controllers <NUM> may be utilized for control of the flash position lamps. For example, a first controller <NUM> may be disposed locally with flash position lamps <NUM>, <NUM>, a second controller <NUM> may be disposed locally with flash position lamps <NUM>, <NUM>, and a third controller <NUM> may be disposed locally with flash position lamp <NUM>.

In various embodiments, controller <NUM> may be configured to control the power (e.g., an input signal) supplied to flash position lamps <NUM>, <NUM>. The power received by flash position lamp <NUM> or flash position lamp <NUM> may take one of two forms as illustrated by waveforms <NUM>, <NUM> in <FIG>. The state of each flash position lamp <NUM>, <NUM> may be determined by a change in direction of travel, or a desired change in direction of travel, of aircraft <NUM>.

With combined reference to <FIG> and <FIG>, flash position lamp <NUM> may be continuously powered on in response to aircraft <NUM> traveling straight, as illustrated by waveform <NUM> (also referred to herein as a first waveform). Flash position lamp <NUM> may be continuously powered off in response to aircraft <NUM> traveling straight, as illustrated by waveform <NUM>. However, during a turning maneuver, the input signal sent to flash position lamp <NUM> may be pulsed, as shown by waveform <NUM> (also referred to herein as a second waveform). Similarly, during a turning maneuver, the input signal sent to flash position lamp <NUM> may be pulsed, as shown by waveform <NUM>. Waveform <NUM> and waveform <NUM> alternate between HIGH and LOW values such that at least one of waveform <NUM> and waveform <NUM> is HIGH at all times. In this manner, an intensity output at the left wing tip, via flash position lamps <NUM>, <NUM> is greater than a desired intensity <NUM>. In various embodiments, desired intensity <NUM> may be measured in units of candela. In various embodiments, the desired intensity <NUM> may be a federal aviation regulation (FAR) requirement. In various embodiments, the desired intensity <NUM> in the direction of flight is <NUM> candela. In various embodiments, the desired intensity <NUM> in the aft direction is <NUM> candela. In various embodiments, the term "desired intensity" as used herein may refer to a maximum intensity of a flash position light when viewed from an angle of zero degrees from the longitudinal axis of the aircraft - i.e., in the line of flight of the aircraft.

In various embodiments, in response to controller <NUM> detecting a change, or desired change, in direction of aircraft <NUM>, waveform <NUM> may sharply increase (e.g., step) to a HIGH value to increase a light intensity of flash position lamp <NUM> above the desired intensity <NUM>. Both waveform <NUM> and waveform <NUM> may be HIGH for a short duration, such as between <NUM> and <NUM> milliseconds for example, and then waveform <NUM> may sharply decrease (e.g., step) to a LOW value (e.g., zero volts) for a duration D1. In various embodiments, duration D1 may be between <NUM> and <NUM> milliseconds. In various embodiments, duration D1 may be between <NUM> and <NUM> milliseconds. In various embodiments, duration D1 may be between <NUM> and <NUM> milliseconds. After duration D1, waveform <NUM> may sharply increase (e.g., step) to a HIGH value to increase a light intensity of flash position lamp <NUM> above the desired intensity <NUM> for a duration D4. Both waveform <NUM> and waveform <NUM> may again be HIGH for a short duration, and then waveform <NUM> may sharply decrease (e.g., step) to a LOW value (e.g., zero volts) for a duration D3. Accordingly, waveform <NUM> may be HIGH for a duration D2. Duration D2 may be greater than duration D1. Duration D3 may be less than duration D2. Duration D3 may be less than duration D1. In this manner, controller <NUM> causes flash position lamps <NUM>, <NUM> to flash in an alternating pattern, while maintaining a light intensity above the desired intensity.

In various embodiments, waveform <NUM> may comprise pulse train comprising a first period T1 and a first duty cycle <NUM>. Waveform <NUM> may comprise pulse train comprising a second period T2 and a second duty cycle <NUM>. In various embodiments, first period T1 is equal to second period T2. In various embodiments, first duty cycle <NUM> is less than second duty cycle <NUM>.

At relatively close distances (e.g., within one hundred yards (<NUM>)) from aircraft <NUM>, an observer may appreciate the change in location of the source of light (i.e., between flash position lamp <NUM> and flash position lamp <NUM>) which may be located within inches (e.g., between six and forty-eight inches (<NUM> - <NUM>)) of each other. However, at relatively far distances (e.g., beyond one hundred yards (<NUM>)) from aircraft <NUM>, it may be difficult for an observer to appreciate the change in location of the source of light (i.e., between flash position lamp <NUM> and flash position lamp <NUM>). However, as illustrated by waveform <NUM>, the compound intensity as the system of lights (i.e., the combined intensity of flash position lamp <NUM> and flash position lamp <NUM>) may generate pulse waves comprising a sum of the intensities of light generated by flash position lamp <NUM> and flash position lamp <NUM> which may be appreciated at relatively far distances. In this manner, waveform <NUM> is always above the desired intensity <NUM>. In this regard, the overlapping portions of waveforms <NUM>, <NUM> generate pulses comprising the sum of waveform <NUM> and <NUM>. Stated differently, the overlapping durations of light emitted from flash position lamp <NUM> and flash position lamp <NUM> generate pulses of light intensity comprising the sum of the intensity of light emitted from flash position lamp <NUM> and flash position lamp <NUM>.

With combined reference to <FIG> and <FIG>, flash position lamp <NUM> may be continuously powered on in response to aircraft <NUM> traveling straight, as illustrated by waveform <NUM>. Flash position lamp <NUM> may be continuously powered off in response to aircraft <NUM> traveling straight, as illustrated by waveform <NUM>. Stated differently, controller <NUM> may be configured to power flash position lamp <NUM> in a continuous ON mode (i.e., turned on) before a change in direction, and may be configured to operate flash position lamp <NUM> in a continuous OFF mode (i.e., turned off) before the change in direction (see waveforms <NUM>, <NUM> during the straight phase of <FIG>). However, during a turning maneuver, the input signal sent to flash position lamp <NUM> may be pulsed, as shown by waveform <NUM>, while the input signal sent to flash position lamp <NUM> may remain constant, as shown by waveform <NUM>. In this manner, a combined intensity output at the left wing tip, via flash position lamps <NUM>, <NUM>, as illustrated by waveform <NUM>, is greater than a desired intensity <NUM>. In various embodiments, desired intensity <NUM> may be measured in units of candles. In various embodiments, the desired intensity <NUM> may be a federal aviation regulation (FAR) requirement. In various embodiments, in response to controller <NUM> detecting a change, or desired change, in direction of aircraft <NUM>, waveform <NUM> may take the form of a pulse train. In various embodiments, a period of pulse waveform <NUM> is constant.

With combined reference to <FIG> and <FIG>, flash position lamp <NUM> may be continuously powered on in response to aircraft <NUM> traveling straight, as illustrated by waveform <NUM>. Flash position lamp <NUM> may be continuously powered off in response to aircraft <NUM> traveling straight, as illustrated by waveform <NUM>. However, during a turning maneuver, the input signal sent to flash position lamp <NUM> may be pulsed, as shown by waveform <NUM>, while the input signal sent to flash position lamp <NUM> may remain constant, as shown by waveform <NUM>. In this manner, a combined intensity output at the left wing tip, via flash position lamps <NUM>, <NUM>, as illustrated by waveform <NUM>, is greater than a desired intensity <NUM>. In various embodiments, desired intensity <NUM> may be measured in units of candles. In various embodiments, the desired intensity <NUM> may be a federal aviation regulation (FAR) requirement. In various embodiments, in response to controller <NUM> detecting a change, or desired change, in direction of aircraft <NUM>, waveform <NUM> may take the form of a pulse train. In various embodiments, a period of pulse waveform <NUM> varies, for example, to create paired pulses <NUM>.

In various embodiments, with reference to <FIG>, waveforms <NUM>, <NUM> may be used for flash position lamps <NUM>, <NUM> to indicate a left-hand turn and waveforms <NUM>, <NUM> may be used for flash position lamps <NUM>, <NUM> to indicate a right-hand turn. In this manner, an observer may recognize the change in direction by either a constant flashing (waveform <NUM>), thereby indicating a left-hand turn, or a double flashes (waveform <NUM>), thereby indicating a right-hand turn. It should be noted that it is contemplated herein that a constant flash (waveform <NUM>) may be used to indicate a right-hand turn and a double flash (waveform <NUM>) may be used to indicate a left-hand turn, and vice-versa.

Furthermore, by using a flash pattern (e.g., constant flashes, double flashes, etc.), waveforms <NUM>, <NUM> may be used for flash position lamps <NUM>, <NUM>, <NUM>, <NUM>, <NUM> to indicate a left-hand turn and waveforms <NUM>, <NUM> may be used for flash position lamps <NUM>, <NUM>, <NUM>, <NUM>, <NUM> to indicate a right-hand turn, and vice-versa. In this regard, instead of flashing only the left wing-tip flash position lamps <NUM>, <NUM> to indicate a left-hand turn (or flashing only the right wing-tip flash position lamps <NUM>, <NUM> to indicate a right-hand turn), all of the flash position lamps <NUM>, <NUM>, <NUM>, <NUM>, <NUM> may be used to provide an indication of a change in heading, thereby broadcasting the turn signal to a broader field of view. Furthermore, by using a flash pattern (e.g., constant flashes, double flashes, etc.) an observer need to recognize which side of the aircraft the signal is coming from, but can determine the change in heading simply by recognizing a pre-determined pattern.

It is noted that the waveforms illustrated in <FIG> may represent both the form of the input signal sent to the flash position lamps, as well as a light intensity output from the respective flash position lamp.

With reference to <FIG>, a method <NUM> for signaling a change in direction for an aircraft is provided, in accordance with various embodiments. Method <NUM> includes alternating power between first and second flash position lamps (step <NUM>). Method <NUM> includes maintaining a combined output intensity of the first and second flash position lamps above a desired intensity (step <NUM>).

With combined reference to <FIG>, <FIG>, and <FIG>, step <NUM> may include alternating electric power (i.e., via electric current and/or voltage) between first and second flash position lamps <NUM>, <NUM>. Step <NUM> may include continuously maintaining the combined output intensity (i.e., the sum of the light output intensity of flash position lamps <NUM>, <NUM>) of first and second flash position lamps <NUM>, <NUM> above desired intensity <NUM>. Step <NUM> and step <NUM> may be performed simultaneously.

With reference to <FIG>, a method <NUM> for signaling a change in direction for an aircraft is provided, in accordance with various embodiments. Method <NUM> includes powering a first flash position lamp disposed at a wing tip in a continuous mode (step <NUM>). Method <NUM> includes powering a second flash position lamp disposed at the wing tip in a flashing mode (step <NUM>).

With combined reference to <FIG>, <FIG>, and <FIG>, step <NUM> may include powering first flash position lamp <NUM> disposed at wing tip <NUM> in a continuous mode. The term "continuous mode," as used herein, may refer to a constant output intensity of a flash position lamp, as illustrated by waveform <NUM>. Step <NUM> may include powering second flash position lamp <NUM> disposed at the wing tip <NUM> in a flashing mode. The term "flashing mode," as used herein, may refer to a varying output intensity of a flash position lamp, commonly referred to as "flashing" or "blinking. " The flashes may be uniform as illustrated by waveform <NUM> or may be clustered as illustrated by waveform <NUM>. In this manner, the combined light output intensity is perceived as flashing, while maintaining the combined light output intensity above the desired intensity <NUM>.

Having described various method for indicating a change in direction of an aircraft using a pair of flash position lamps disposed at each wing tip, it is further contemplated that a single flash position lamp (one at each wing tip) may be used for indicating a change in direction of the aircraft. With combined reference to <FIG> and <FIG>, a method for signaling a change in direction for an aircraft may be similar to the methods described herein, except that both input signals (e.g., waveforms <NUM>, <NUM>, waveforms <NUM>, <NUM> (see <FIG>), and waveforms <NUM>, <NUM> (see <FIG>)) are supplied to a single flash position lamp. In this regard, a method for signaling a change in direction for an aircraft may include controlling flash position lamp <NUM> and flash position lamp <NUM> for indicating either a left or right turn. Flash position lamp <NUM> or flash position lamp <NUM> may be configured to flash such that the output intensity is similar to that of waveform <NUM>. In this regard, the output intensity may be varied between a first value <NUM> which is greater than desired intensity <NUM> and a second value <NUM> which is greater than first value <NUM>. In this regard, flash position lamp <NUM> and/or flash position lamp <NUM> may be operated in a flashing mode while maintaining the output intensity of flash position lamp <NUM> and/or flash position lamp <NUM> above output intensity <NUM>. Flash position lamp <NUM> and/or flash position lamp <NUM> may similarly be operated to flash as illustrated by waveform <NUM> of <FIG> and/or waveform <NUM> as illustrated in <FIG>, as described herein.

As described herein, flash position lamp <NUM> may be operated in a flashing mode and flash position lamp <NUM> may be operated in continuous mode to indicate the change in direction of the aircraft, or both flash position lamp <NUM> and flash position lamp <NUM> may be operated in a flashing mode to indicate the change in direction of the aircraft (e.g., see <FIG>).

However, the benefits, advantages, solutions to problems, and any elements that may cause any benefit, advantage, or solution to occur or become more pronounced are not to be construed as critical, required, or essential features or elements of the disclosures. The scope of the disclosures is accordingly to be limited by nothing other than the appended claims and their legal equivalents, in which reference to an element in the singular is not intended to mean "one and only one" unless explicitly so stated, but rather "one or more.

In the detailed description herein, references to "various embodiments", "one embodiment", "an embodiment", "an example embodiment", etc., indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic.

Claim 1:
An aircraft (<NUM>), comprising:
a first pair of forward-facing flash position lamps (<NUM>, <NUM>) disposed at a first wing tip (<NUM>), the first pair of flash position lamps comprising a first flash position lamp and a second flash position lamp;
a second pair of forward-facing flash position lamps (<NUM>, <NUM>) disposed at a second wing tip (<NUM>), the second pair of flash position lamps comprising a third flash position lamp and a fourth flash position lamp; and
a controller (<NUM>) in electronic communication with the first pair of flash position lamps, wherein at least one of the first flash position lamp and the second flash position lamp are configured to flash, while maintaining a combined intensity of the first pair of forward-facing flash position lamps above a desired intensity, to indicate a change in direction of the aircraft,
wherein each flash position lamp may be operated in a continuous mode and/or a flashing mode.