Patent Description:
Aircraft generally include exterior lights, such as anti-collision lights, landing taxi lights, or the like, which are located on an exterior of the aircraft to, for example, visually indicate the aircraft is in the vicinity. The exterior aircraft lights may employ light emitting diodes (LEDs). One of the design considerations for LEDs is heat dissipation, as overheating can lead to temporary malfunction and/or permanent damage to the LEDs. <CIT> relates to an aircraft lighting unit using LEDs. More particularly, the document discloses a warning lamp for an aircraft with a housing which possesses a light permeable cover that is exposed to the surrounding air when the housing is mounted on the aircraft, and a cooling body for the at least one LED, wherein the cooling body possesses a cooling surface that is exposed to the surrounding air when the housing is mounted on the aircraft. <CIT> relates to an LED searchlight.

A light assembly is provided in claim <NUM>. In accordance with various embodiments, the light assembly comprises a heatsink, a plurality of light emitting diodes, and a lens. The heatsink includes a first surface and a second surface opposite the first surface. The second surface defines an airflow path extending from a first end of the heatsink to a second end of the heatsink. The plurality of light emitting diodes are coupled to the first surface of the heatsink. The lens is located over the plurality of light emitting diodes and may contact the heatsink. The lens includes a first cutout proximate the first end of the heatsink and a second cutout proximate the second end of the heatsink.

In various embodiments, a plurality of fins may extend from the second surface of the heatsink. In various embodiments, the light assembly may further comprise an aircraft mount including a base plate. The heatsink may be located over an upper surface of the base plate.

In various embodiments, a first fin of the plurality of fins may extend to the upper surface of the base plate. In various embodiments, a central support structure may be coupled between the plurality of fins and the upper surface of the base plate.

In various embodiments, the aircraft mount may further include a lens bezel coupled to the base plate. The lens may form a sealing interface with the lens bezel.

In various embodiments, the heatsink may include a first radially extending lip formed at the first end of the heatsink and a second radially extending lip formed at the second end of the heatsink. At least, a portion of the first radially extending lip and, at least, a portion of the second radially extending lip may be located exterior to the lens.

An aircraft light assembly is also disclosed herein. In accordance with various embodiments, the aircraft light assembly may comprise an aircraft mount, a light emitting diode assembly located over an upper surface of the aircraft mount, and a lens. The light emitting diode assembly may include a heatsink located on the upper surface of the aircraft mount. The heatsink may comprise a first surface, a second surface opposite the first surface, and a plurality of light emitting diodes coupled to the first surface. The second surface may define an airflow path extending from a first end of the heatsink to a second end of the heatsink. The lens may be located over the plurality of light emitting diodes. The lens may contact the heatsink.

In various embodiments, the light emitting diode assembly may further comprise a circuit board mounted on the first surface of the heatsink. The plurality of light emitting diodes may be electrically connected to the circuit board.

In various embodiments, the first surface of the heatsink may form a convex curve extending from the upper surface of the aircraft mount. In various embodiments, the second surface of the heatsink may form a concave curve extending from the upper surface of the aircraft mount.

In various embodiments, the heatsink may further comprise a plurality of fins extending inward from the second surface of the heatsink. In various embodiments, a first fin of the plurality of fins may extend to the upper surface of the aircraft mount.

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 exemplary embodiments of the disclosure, it should be understood that 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, when falling within the scope of the appended claims. Thus, the detailed description herein is presented for purposes of illustration only and not limitation.

Also, any reference to attached, fixed, connected or the like may include permanent, removable, temporary, partial, full, and/or any other possible attachment option.

Throughout the present disclosure, like reference numbers denote like elements. Accordingly, elements with like element numbering may be shown in the figures, but may not be necessarily repeated herein for the sake of clarity.

As used herein, "aft" refers to the direction associated with the tail (i.e., the back end) of an aircraft, or generally, to the direction of exhaust of a gas turbine engine. As used herein, "forward" refers to the direction associated with a nose (i.e., the front end) of an aircraft, or generally, to the direction of flight or motion.

With reference to <FIG>, an aircraft <NUM> having a fuselage <NUM>, wings <NUM>, and a tail <NUM> is illustrated. Aircraft <NUM> may be a fixed wing aircraft. In accordance with various embodiments, one or more aircraft light assemblies <NUM> may be mounted to the exterior of aircraft <NUM>. For example, light assemblies <NUM> may be mounted to fuselage <NUM>, wings <NUM> and/or tail <NUM>. Light assemblies <NUM> may be employed as anti-collision lights, forward and/or tail positions lights (often referred to navigation lights), emergency exit lights, ground recognition beacons, landing and taxi lights, or any other exterior light of aircraft <NUM>.

With reference to <FIG>, in various embodiments, light assemblies <NUM> may be coupled to an aircraft <NUM>. Aircraft <NUM> may be a rotor aircraft (e.g., a helicopter). Aircraft <NUM> may include a fuselage <NUM>, a main rotor <NUM>, a tail <NUM>, and a tail rotor <NUM>. In accordance with various embodiments, one or more light assemblies <NUM> may be mounted to the exterior of aircraft <NUM>. For example, light assemblies <NUM> may be mounted to fuselage <NUM> and/or tail <NUM>. Light assemblies <NUM> may be employed as anti-collision lights, forward and/or tail positions lights, emergency exit lights, ground recognition beacons, landing and taxi lights, or any other exterior light of aircraft <NUM>.

As described in further detail below, light assemblies <NUM> include LEDs attached to a thermally conductive base (or heatsink) and covered with a translucent shell (or lens). In accordance with various embodiments, the heatsink may include fins. Heat generated during operation of the LEDs is transferred via conduction to the fins. The fins are open to the external environment and dissipate the heat from the LEDs to the surrounding ambient air (e.g., via convection). Stated differently, light assemblies <NUM> are configured to cause heat, which is transferred from the LEDS to the heatsink, to be exchanged with external air flowing through the heatsink. As used herein "external air" refers to air outside of the aircraft (e.g., air flowing over the exterior surfaces of the aircraft). Light assemblies <NUM> thus reduce, or eliminate, the need to conduct heat to the airframe. The thermal management (e.g., heat dissipation) capabilities of light assemblies <NUM> allow light assemblies <NUM> to be employed in larger wattage applications (e.g., applications of <NUM> watts or greater) and/or in locations where natural convection and conductive thermal sinking to the aircraft is insufficient and/or where active cooling is not an option.

With reference to <FIG>, <FIG>, and <FIG> an exemplary aircraft light assembly <NUM> is shown, in accordance with various embodiments. Light assembly <NUM> may comprise an LED assembly <NUM>, an aircraft mount <NUM>, and a lens <NUM>. Aircraft mount <NUM> may include a base plate <NUM> and a lens bezel <NUM>. LED assembly <NUM> may be coupled (e.g., mounted) to base plate <NUM>. Base plate <NUM> may be coupled (e.g., mounted) to lens bezel <NUM>. Base plate <NUM> may be attached to an underside (or first) surface <NUM> of lens bezel <NUM> via screws, nuts and bolts, clips, adhesive, and/or any other suitable securement means. LED assembly <NUM> and lens <NUM> are located over an upper (or first) surface <NUM> of base plate <NUM>. Aircraft mount <NUM> is configured to be coupled to an exterior surface of aircraft <NUM> or aircraft <NUM> in <FIG>, respectively. Stated different, light assembly <NUM> is coupled to aircraft <NUM> or aircraft <NUM> by attaching aircraft mount <NUM> to an exterior surface of an aircraft structure (e.g., to an exterior surface of fuselage <NUM>, wings <NUM>, tail <NUM>, fuselage <NUM> or tail <NUM>). Aircraft mount <NUM> (e.g., lens bezel <NUM> and/or base plate <NUM>) may be attached to the aircraft structure via screws, nuts and bolts, clips, adhesive, and/or any other suitable securement means.

LED assembly <NUM> includes a heatsink (or base) <NUM> and a plurality of LEDs <NUM> coupled to heatsink <NUM>. In various embodiments, LEDs <NUM> may be located on one or more LED circuit board(s) <NUM> mounted to heatsink <NUM>. Heatsink <NUM> may be coupled to upper surface <NUM> of base plate <NUM> via welding, screws, nuts and bolts, clips, adhesive, and/or any other suitable securement means.

While base plate <NUM>, lens bezel <NUM>, and heatsink <NUM> are illustrated as separate, discrete structures, it is contemplated and understood that, in various embodiments, base plate <NUM>, lens bezel <NUM>, and/or heatsink <NUM> may be formed as a single, integral structure. For example, in various embodiments, heatsink <NUM> may be integral to base plate <NUM>. In this regard, base plate <NUM> and heatsink <NUM> may be manufactured via milling, casting, molding, additive manufacturing, etc. as a single part, rather than manufacturing heatsink <NUM> and base plate <NUM> as separate parts and then attaching heatsink <NUM> to base plate <NUM>. In various embodiments, base plate <NUM> may be integral to lens bezel (e.g., base plate <NUM> and lens bezel <NUM> may be manufactured via milling, casting, molding, additive manufacturing, etc. as a single part, rather than manufacturing lens bezel <NUM> and base plate <NUM> as separate parts and then attaching lens bezel <NUM> to base plate <NUM>). In various embodiments, heatsink <NUM> may be integral to lens bezel (e.g., lens bezel <NUM> and heatsink <NUM> may be manufactured via milling, casting, molding, additive manufacturing, etc. as a single part, and base plate <NUM> may then be coupled to the single part). In various embodiments, heatsink <NUM> may be integral to base plate <NUM>, and base plate <NUM> may be integral to lens bezel (e.g., heatsink <NUM>, base plate <NUM>, and lens bezel may be manufactured via milling, casting, molding, additive manufacturing, etc. as a single part).

Lens <NUM> is located over and covers LEDs <NUM> and LED circuit board(s) <NUM>. Lens <NUM> extends to and/or contacts heatsink <NUM> and lens bezel <NUM>. In various embodiments, a flange <NUM> of lens <NUM> may be located under lens bezel <NUM>. For example, flange <NUM> may be located (e.g., sandwiched) between lens bezel <NUM> and upper surface <NUM> of base plate <NUM>. In various embodiments, an inner circumferential surface <NUM> of lens bezel <NUM> may define a recess configured to receive flange <NUM> of lens <NUM>. Lens <NUM> is configured to form a sealing interface with heatsink <NUM> and lens bezel <NUM>. For example, in various embodiments, lens <NUM> may form a hermetic seal with lens bezel <NUM> and/or heatsink <NUM>. Lens <NUM> protects the circuity of circuit boards <NUM> and LEDs <NUM>. Lens <NUM> may also be configured to distribute light emitted from LEDs <NUM>.

In accordance with various embodiments, LEDs <NUM> are located over a first (or outer) surface <NUM> of heatsink <NUM>. First surface <NUM> is opposite (i.e., oriented away from) a second (or inner) surface <NUM> of heatsink <NUM>. In various embodiments, first surface <NUM> may comprise a curved shape. Stated differently, first surface <NUM> may form a convex (or c-shaped) surface extending from upper surface <NUM> of base plate <NUM>. While first surface <NUM> is illustrated as having a generally semi-circular (or C-shaped) cross-section, it is contemplated and understood that first surface <NUM> may be oriented in other geometries. For example, first surface <NUM> may have multiple curvatures and/or portions oriented at a variety of angles relative to one another, depending on the desired configuration of LEDs <NUM>.

First surface <NUM> and second surface <NUM> may each extend from a first end <NUM> of heatsink <NUM> to a second end <NUM> of heatsink <NUM>. Second end <NUM> is axially opposite first end <NUM>. In various embodiments, a radially extending lip, or flange, <NUM> may be formed at each of first end <NUM> and second end <NUM>. Each Lip <NUM> may include a first radial surface <NUM> extending radially from first surface <NUM>, a second radial surface <NUM> extending radially from second surface <NUM>, and an outer circumferential surface <NUM> extending axially between first radial surface <NUM> and second radial surface <NUM>. First radial surface <NUM> may be approximately parallel to second radial surface <NUM> and approximately normal to first surface <NUM>. As used in the previous context only, "approximately parallel" means ±<NUM>° from parallel and "approximately normal" means ±<NUM>° from normal.

First surface <NUM> extends axially from the first radial surface <NUM> at first end <NUM> of heatsink <NUM> to the first radial surface <NUM> at second end <NUM> of heatsink <NUM>. Second surface <NUM> extends axially from the second radial surface <NUM> at first end <NUM> of heatsink <NUM> to the second radial surface <NUM> at second end <NUM> of heatsink <NUM>. A distance, or thickness, of heatsink <NUM> between second surface <NUM> and outer circumferential surface <NUM> is greater than the distance, or thickness, of heatsink <NUM> between second surface <NUM> and first surface <NUM>. In various embodiments, inner circumferential surface <NUM> of lens bezel <NUM> may extend to and/or contact second radial surface <NUM> at first end <NUM> of heatsink <NUM>. Inner circumferential surface <NUM> may also extend to and/or contact second radial surface <NUM> at second end <NUM> of heatsink <NUM>.

In various embodiments, lens <NUM> extends to and/or contacts the outer circumferential surface <NUM> of lips <NUM>. In various embodiments, lens <NUM> extends to and/or contacts first surface <NUM> of heatsink <NUM>, such that lips <NUM> are outside, or exterior to, lens <NUM>. In various embodiments, lens <NUM> may also contact first radial surface <NUM>. In various embodiments, first radial surface <NUM> may define a recess configured to receive a flange of lens <NUM>. Lips <NUM> (e.g., first radial surfaces <NUM>) tend to provide an increased surface area for generating a sealing interface between heatsink <NUM> and lens <NUM>. Lips <NUM> may also be configured to block light emitted from one or more LEDs <NUM> in one or more desired directions.

Lens <NUM> includes a first cutout <NUM> (or contoured surface) at first end <NUM> of heatsink <NUM> and a second cutout (or contoured surface), similar to first cutout <NUM>, at second end <NUM> of heatsink <NUM>. In various embodiments, the shape of the first and second cutouts mirrors, or complements, the shape of first surface <NUM> of heatsink <NUM>. The first and second cutouts are configured to allow lens <NUM> to contact and/or form a sealing interface with heatsink <NUM>, while allowing fluid (e.g., air) exterior to lens <NUM> to flow through heatsink <NUM> (e.g., to flow from first end <NUM> to second end <NUM> along second surface <NUM>).

In accordance with various embodiments, second surface <NUM> defines an airflow path under LEDs <NUM>. The configuration of heatsink <NUM> and lens <NUM> allows fluid (e.g., ambient air) that is exterior to lens <NUM> to flow across second surface <NUM> of heatsink <NUM> (e.g., from first end <NUM> to second end <NUM>), thereby dissipating heat from heatsink <NUM> via convection, while LEDs <NUM> and circuit boards <NUM> remain protected and/or sealed off from the fluid by lens <NUM>. Heatsink <NUM> is formed of material having sufficient thermal conductivity (e.g., a metal or metal alloy such as steel, stainless steel, aluminum, copper, etc.) to allow heat to easily transfer from LEDs <NUM> and circuit boards <NUM> to heatsink <NUM>.

In accordance with various embodiments, heatsink <NUM> includes one or more fin(s) <NUM> extending from second surface <NUM>. Fins <NUM> and second surface <NUM> define a plurality of fluid channels <NUM> extending from first end <NUM> to second end <NUM>. Fluid channels <NUM> fluidly connect the exterior area of lens <NUM> proximate first end <NUM> and the exterior area of lens <NUM> proximate second end <NUM>. Fins <NUM> may extend axially from first end <NUM> to second end <NUM> of heatsink <NUM>. Fins <NUM> increase the surface area of heatsink <NUM> that is exposed to the air flowing between first end <NUM> and second end <NUM>, thereby increasing the surface area for heat transfer to the air. In various embodiments, fins <NUM> may be connected to a central support structure <NUM>. Central support structure <NUM> may extend to and/or contact upper surface <NUM> of base plate <NUM>. In various embodiments, central support structure <NUM> may be eliminated from heatsink <NUM>, and fins <NUM> may terminate prior to contact with one other. The number of fins <NUM> and the arrangement of fins <NUM> along second surface <NUM> in <FIG>, <FIG>, <FIG>, is an example fin arrangement, it is contemplated and understood that any number of fins and/or fins in other arrangements may be employed. In accordance with various embodiments, the thickness each fin <NUM>, the length each fin <NUM> (as measured from second surface <NUM>), and the location on second surface <NUM> of each fin <NUM> are selected such that an equal, or almost equal, amount of thermal energy passes through each fin <NUM> for even exposure in the fluid channels <NUM>.

The configuration of heatsink <NUM> and lens <NUM> creates an environmental air flow path through light assembly <NUM> that allows heat generated by LEDs <NUM> to be exchanged with cooler free-flowing air (or forced air exhibited during flight), thereby decreasing, or eliminating, the need to conduct the heat to the airframe, while still protecting LEDs <NUM> and circuit boards <NUM> from exposure to elements (e.g., dust, debris, water, etc.) outside lens <NUM>.

With combined reference to <FIG> and <FIG>, in various embodiment, one or more of aircraft light assemblies <NUM> may be mounted to aircraft <NUM> such that the airflow <NUM> generated by main rotor <NUM> is forced through fluid channels <NUM>. For example, aircraft light assemblies <NUM> may be oriented such that the flow direction through fluid channels <NUM> is parallel to the direction of airflow <NUM> from main rotor <NUM>. In this regard, aircraft mount <NUM> may be mounted to fuselage <NUM> or tail <NUM> such that the second radial surface <NUM> of either first end <NUM> or second end <NUM> of heatsink <NUM> is oriented toward the main rotor <NUM>. Stated differently, second surface <NUM> of heatsink <NUM> may be approximately parallel to the axis of rotation of main rotor <NUM>, and second radial surface <NUM> may be approximately perpendicular to the axis of rotation of main rotor <NUM>. As used in the previous context only, "approximately parallel" means ± <NUM>° from parallel and "approximately perpendicular" means ±<NUM>° from perpendicular. Flowing the airflow <NUM> generated by main rotor <NUM> through fluid channels <NUM> tends to increase the thermal efficiency of aircraft light assemblies <NUM>.

With combined reference to <FIG> and <FIG>, in various embodiments, one or more of aircraft light assemblies <NUM> may be mounted to aircraft <NUM> such that an airflow <NUM> generated during flight of aircraft <NUM> is forced through fluid channels <NUM>. For example, aircraft light assemblies <NUM> may be oriented such that the flow direction through fluid channels <NUM> is parallel to the direction of airflow <NUM> (e.g., parallel to the direction of flight). In this regard, aircraft mount <NUM> may be mounted to fuselage <NUM>, wings <NUM>, or tail <NUM> such that the second radial surface <NUM> of either first end <NUM> or second end <NUM> of heatsink <NUM> is oriented in the forward direction. Stated differently, second surface <NUM> of heatsink <NUM> may be approximately parallel to an axis extending in the forward-to-aft direction, and second radial surface <NUM> may be approximately perpendicular to an axis extending in the forward-to-aft direction. As used in the previous context only, "approximately parallel" means ± <NUM>° from parallel and "approximately perpendicular" means ±<NUM>° from perpendicular. Flowing the airflow <NUM> generated during flight through fluid channels <NUM> tends to increase the thermal efficiency of aircraft light assemblies <NUM>.

With reference to <FIG>, an aircraft light assembly <NUM> is shown. Aircraft <NUM> in <FIG> and/or aircraft <NUM> in <FIG> may include light assembly <NUM> in place of one or more of the light assemblies <NUM>. Light assembly <NUM> may comprise an LED assembly <NUM>, an aircraft mount <NUM>, and a lens <NUM>. Aircraft mount <NUM> includes a base plate <NUM>. In various embodiments, aircraft mount <NUM> may also include a lens bezel, similar to lens bezel <NUM> of aircraft mount <NUM> in <FIG> and <FIG>, and lens <NUM> may form a sealing interface with the lens bezel, similar to lens <NUM> in <FIG> and <FIG>.

LED assembly <NUM> and lens <NUM> are located over an upper (or first) surface <NUM> of base plate <NUM>. Aircraft mount <NUM> is configured to be coupled to an exterior surface of aircraft <NUM> or aircraft <NUM> in <FIG>, respectively. Stated different, light assembly <NUM> is coupled to aircraft <NUM> or aircraft <NUM> by attaching aircraft mount <NUM> to an exterior surface of an aircraft structure (e.g., to an exterior surface of fuselage <NUM>, wings <NUM>, tail <NUM>, fuselage <NUM> or tail <NUM>). Aircraft mount <NUM> (e.g., base plate <NUM>) may be attached to the aircraft structure via screws, nuts and bolts, clips, adhesive, and/or any other suitable securement means.

LED assembly <NUM> includes a heatsink (or base) <NUM> and a plurality of LEDs <NUM> coupled to heatsink <NUM>. In various embodiments, LEDs <NUM> may be located on one or more LED circuit board(s) <NUM>, which are mounted to heatsink <NUM>. Heatsink <NUM> may be coupled to upper surface <NUM> of base plate <NUM> via welding, screws, nuts and bolts, clips, adhesive, and/or any other suitable securement means.

While base plate <NUM> and heatsink <NUM> are illustrated as separate, discrete structures, it is contemplated and understood that, in various embodiments, base plate <NUM> and heatsink <NUM> may be formed as a single, integral structure. For example, in various embodiments, heatsink <NUM> may be integral to base plate <NUM>. In this regard, base plate <NUM> and heatsink <NUM> may be manufactured via milling, casting, molding, additive manufacturing, etc. as a single part, rather than manufacturing heatsink <NUM> and base plate <NUM> as separate parts and then attaching heatsink <NUM> to base plate <NUM>.

Lens <NUM> may be located over LEDs <NUM> and LED circuit board(s) <NUM>. Lens <NUM> extends to and/or contacts heatsink <NUM>. In various embodiments, lens <NUM> extends to and contacts upper surface <NUM> of base plate <NUM>. Lens <NUM> is located over and covers LEDs <NUM> and LED circuit board(s) <NUM>. In this regard, lens <NUM> may protect the circuity of circuit boards <NUM> and LEDs <NUM> from elements external to lens <NUM>. Lens <NUM> may also be configured to distribute light emitted from LEDs <NUM>.

In accordance with various embodiments, LEDs <NUM> are located over a first (or outer) surface <NUM> of heatsink <NUM>. First surface <NUM> is opposite (i.e., oriented away from) a second (or inner) surface <NUM> of heatsink <NUM>. In various embodiments, first surface <NUM> may comprise a plurality of planar (e.g., flat) sections oriented at varying angles. In various embodiments, second surface <NUM> may be oriented in a curve. For example, second surface <NUM> may form a concave (or C-shaped) surface extending from upper surface <NUM> of base plate <NUM>.

First surface <NUM> and second surface <NUM> may each extend from a first end <NUM> of heatsink <NUM> to a second end <NUM> of heatsink <NUM>. Second end <NUM> is axially opposite first end <NUM>. In various embodiments, a first radial surface <NUM> at first end <NUM> of heatsink <NUM> may extend radially between first surface <NUM> and second surface <NUM>. A second radial surface <NUM> at second end <NUM> of heatsink <NUM> may extend radially between first surface <NUM> and second surface <NUM>. In various embodiments, heatsink <NUM> may include one or more attachment flanges <NUM>. Attachment flanges <NUM> may be used to secure heatsink <NUM> to base plate <NUM>.

First radial surface <NUM> may be approximately parallel to second radial surface <NUM> and approximately normal to first surface <NUM> and second surface <NUM>. As used in the previous context only, "approximately parallel" means ±<NUM>° from parallel and "approximately normal" means ±<NUM>° from normal. Each of first surface <NUM> and second surface <NUM> extends axially from the first radial surface <NUM> at first end <NUM> to the second radial surface <NUM> at second end <NUM>.

Lens <NUM> includes a first cutout (or contoured surface) at first end <NUM> of heatsink <NUM> and a second cutout (or contoured surface) at second end <NUM> of heatsink <NUM>. The perimeter of lens <NUM>, including the first and second cutouts, is configured to allow lens <NUM> to contact and/or form a sealing interface with heatsink <NUM>, while allowing fluid exterior to lens <NUM> to flow through heatsink <NUM> (i.e., along second surface <NUM> and from first end <NUM> to second end <NUM>). In various embodiments, lens <NUM> may extend to and/or contact first radial surface <NUM> and second radial surface <NUM> such that first radial surface <NUM> and second radial surface <NUM> are inside (or interior to) lens <NUM>, and the first and second cutouts in lens <NUM> may have a shape that mirrors (or complements) the shape of second surface <NUM> of heatsink <NUM>. In various embodiments, lens <NUM> may extend to and/or contact first surface <NUM> such that first radial surface <NUM> and second radial surface <NUM> are outside (or exterior to) lens <NUM>, and the first and second cutouts in lens <NUM> have a shape that mirrors (or complements) the shape of first surface <NUM> of heatsink <NUM>. In various embodiments, lens <NUM> may also contact and form a sealing interface with base plate <NUM>.

In accordance with various embodiments, second surface <NUM> defines an airflow path under LEDs <NUM>. The configuration of heatsink <NUM> and lens <NUM> allows fluid (e.g., ambient air) that is exterior to lens <NUM> to flow across second surface <NUM> of heatsink <NUM> (e.g., from first end <NUM> to second end <NUM>), thereby dissipating heat from heatsink <NUM> via convection, while LEDs <NUM> and circuit boards <NUM> remain protected and/or sealed off from the fluid by lens <NUM>. Heatsink <NUM> is formed of material having good thermal conductivity (e.g., a metal or metal alloy) to allow heat to easily transfer from LEDs <NUM> and circuit boards <NUM> to heatsink <NUM>.

In accordance with various embodiments, heatsink <NUM> includes one or more fin(s) <NUM> extending from second surface <NUM>. Fins <NUM> and second surface <NUM> define a plurality of fluid channels <NUM> extending from first end <NUM> to second end <NUM>. Fluid channels <NUM> fluidly connect the exterior area of lens <NUM> proximate first end <NUM> of heatsink <NUM> and the exterior area of lens <NUM> proximate second end <NUM> of heatsink <NUM>. Fins <NUM> may axially extend from first end <NUM> to second end <NUM> of heatsink <NUM>. In various embodiments, fins <NUM> extend to and/or contact upper surface <NUM> of base plate <NUM>. In various embodiments, one or more fin(s) <NUM> may terminate prior to upper surface <NUM>, such that fluid may flow between the bottom end of fin <NUM> (i.e., the end opposite second surface <NUM>) and upper surface <NUM>. Fins <NUM> increase the surface area of heatsink <NUM> that is exposed to the air flowing between first end <NUM> and second end <NUM>, thereby increasing the surface area for heat transfer to the air. In accordance with various embodiments, the thickness each fin <NUM>, the length each fin <NUM> (as measured from second surface <NUM>), and the location on second surface <NUM> of each fin <NUM> may be selected such that an equal, or almost equal, amount of thermal energy passes through each fin <NUM> for even exposure in the fluid channels <NUM>. The configuration of heatsink <NUM> and lens <NUM> creates an environmental air flow path through light assembly <NUM> that allows heat generated by LEDs <NUM> to be exchanged with cooler free-flowing air (or forced air exhibited during flight), thereby decreasing, or eliminating, the need to conduct the heat to the airframe, while still protecting LEDs <NUM> and circuit boards <NUM> from environmental damage.

With combined reference to <FIG> and <FIG>, in various embodiment, one or more of aircraft light assemblies <NUM> may be mounted to aircraft <NUM> such that the airflow <NUM> generated by main rotor <NUM> is forced through fluid channels <NUM>. For example, aircraft light assemblies <NUM> may be oriented such that the flow direction through fluid channels <NUM> is parallel to the direction of airflow <NUM> from main rotor <NUM>. In this regard, aircraft mount <NUM> may be mounted to fuselage <NUM> or tail <NUM> such that either first radial surface <NUM> or second radial surface <NUM> is oriented toward the main rotor <NUM>. Stated differently, second surface <NUM> of heatsink <NUM> may be approximately parallel to the axis of rotation of main rotor <NUM>, and first and second radial surfaces <NUM>, <NUM> may be approximately perpendicular to the axis of rotation of main rotor <NUM>. As used in the previous context only, "approximately parallel" means ± <NUM>° from parallel and "approximately perpendicular" means ±<NUM>° from perpendicular. Flowing the airflow <NUM> generated by main rotor <NUM> through fluid channels <NUM> tends to increase the thermal efficiency of aircraft light assemblies <NUM>.

With combined reference to <FIG> and <FIG>, in various embodiments, one or more of aircraft light assemblies <NUM> may be mounted to aircraft <NUM> such that the airflow <NUM> generated during flight of aircraft <NUM> is forced through fluid channels <NUM>. For example, aircraft light assemblies <NUM> may be oriented such that the flow direction through fluid channels <NUM> is parallel to the direction of airflow <NUM> (e.g., parallel to the direction of flight). In this regard, aircraft mount <NUM> may be mounted to fuselage <NUM>, wings <NUM>, or tail <NUM> such that either first radial surface <NUM> or second radial surface <NUM> is oriented in the forward direction. Stated differently, second surface <NUM> of heatsink <NUM> may be approximately parallel to an axis extending in the forward-to-aft direction, and first and second radial surfaces <NUM>, <NUM> may be approximately perpendicular to an axis extending in the forward-to-aft direction. As used in the previous context only, "approximately parallel" means ± <NUM>° from parallel and "approximately perpendicular" means ±<NUM>° from perpendicular. Flowing the airflow <NUM> generated during flight through fluid channels <NUM> tends to increase the thermal efficiency of aircraft light assemblies <NUM>.

Benefits and other advantages have been described herein with regard to specific embodiments. However, the benefits, advantages, and any elements that may cause any benefit or advantage to occur or become more pronounced are not to be construed as critical, required, or essential features or elements of the disclosure.

Systems, methods, and apparatus are provided herein. 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:
A light assembly, comprising:
a heatsink (<NUM>) including a first surface (<NUM>) and a second surface (<NUM>) opposite the first surface, the second surface defining an airflow path extending from a first end (<NUM>) of the heatsink to a second end (<NUM>) of the heatsink;
a plurality of light emitting diodes (<NUM>) coupled to the first surface (<NUM>) of the heatsink; and
a lens (<NUM>) located over the plurality of light emitting diodes (<NUM>) and contacting to the heatsink (<NUM>), characterised in that
the lens (<NUM>) includes a first cutout proximate the first end of the heatsink and a second cutout proximate the second end of the heatsink.