Dual sided aircraft light assembly

A dual sided aircraft light assembly includes a mount structure, a plurality of first light emitters, a plurality of first optics, a plurality of second light emitters, and a plurality of second optics. The first light emitters are disposed such that, upon being energized, each emits light in a first direction that is at an acute angle relative to a reference line that extends in a reference direction. The first optics are configured to focus the light emitted from the first light emitters into a first light beam directed in the first direction. The second light emitters are disposed such that, upon being energized, each emits light in a second direction that is at an obtuse angle relative to the reference line and reference direction. The second optics focus the light emitted from the second light emitters into a second light beam directed in the second direction.

CROSS-REFERENCE TO RELATED APPLICATION

This application claims priority to India Provisional Patent Application No. 202211010657, filed Feb. 28, 2022, the entire content of which is incorporated by reference herein.

TECHNICAL FIELD

The present invention generally relates to aircraft exterior lighting, and more particularly relates to a dual sided aircraft light assembly.

BACKGROUND

In the aviation industry, the pushback operation is a procedure in which an aircraft is pushed backwards away from its parking position, such as an airport gate, by external power, such as a tractor. To implement the operation, the tractor must be connected to the aircraft and communications must be established between the aircraft and the tractor operator throughout the pushback. Thus, a pushback can take several minutes, which can lead to reduced operational efficiency.

More modern aircraft are being designed with electrical, auto reversible propulsion. These aircraft will thus have onboard capability to pushback, without the need for any external power source. During a nighttime pushback with such onboard capability, proper illumination will be needed so that the aircraft pilot and ground crew can see the entire pushback area. Unfortunately, presently known exterior lights are not capable of illuminating the rear side of the aircraft with a single light when mounted on the landing gear.

Hence, there is a need for an aircraft light assembly that can be mounted on the landing gear of an aircraft and provide illumination both forward and rearward of the aircraft. The present invention addresses at least this need.

BRIEF SUMMARY

In one embodiment, a dual sided aircraft light assembly includes a mount structure, a plurality of first light emitters, a plurality of first optics, a plurality of second light emitters, a plurality of second optics, a first lens, and a second lens. The mount structure is adapted to be mounted to an aircraft landing gear. The first light emitters are coupled to the mount structure. Each first light emitter is disposed such that, upon being electrically energized, each first light emitter emits light in a first direction that is at an acute angle relative to a reference line that extends in a reference direction. The first optics are disposed adjacent to the plurality of first light emitters. Each first optic is associated with and is disposed to receive the light emitted from a different one of the first light emitters. The first optics are configured to focus the light emitted from the first light emitters into a first light beam that is directed in the first direction. The second light emitters are coupled to the mount structure. Each second light emitter is disposed such that, upon being energized, each second light emitter emits light in a second direction that is at an obtuse angle relative to the reference line and the reference direction. The second optics are disposed adjacent to the plurality of second light emitters. Each second optic is associated with and is disposed to receive the light emitted from a different one of the second light emitters. The second optics are configured to focus the light emitted from the second light emitters into a second light beam that is directed in the second direction. The first lens is coupled to and encloses the first light emitters and the first optics. The second lens is coupled to and encloses the second light emitters and the second optics.

In another embodiment, an aircraft includes a fuselage, landing gear coupled to the fuselage, and at least one dual sided aircraft light assembly coupled to at least a portion of the landing gear. The at least one dual sided aircraft light assembly includes a mount structure, a plurality of first light emitters, a plurality of first optics, a plurality of second light emitters, a plurality of second optics, a first lens, and a second lens. The mount structure is mounted on the aircraft landing gear. The first light emitters are coupled to the mount structure. Each first light emitter is disposed such that, upon being electrically energized, each first light emitter emits light in a first direction that is at an acute angle relative to a reference line that extends in a reference direction. The first optics are disposed adjacent to the plurality of first light emitters. Each first optic is associated with and is disposed to receive the light emitted from a different one of the first light emitters. The first optics are configured to focus the light emitted from the first light emitters into a first light beam that is directed in the first direction. The second light emitters are coupled to the mount structure. Each second light emitter is disposed such that, upon being energized, each second light emitter emits light in a second direction that is at an obtuse angle relative to the reference line and the reference direction. The second optics are disposed adjacent to the plurality of second light emitters. Each second optic is associated with and is disposed to receive the light emitted from a different one of the second light emitters. The second optics are configured to focus the light emitted from the second light emitters into a second light beam that is directed in the second direction. The first lens is coupled to and encloses the first light emitters and the first optics. The second lens is coupled to and encloses the second light emitters and the second optics.

Furthermore, other desirable features and characteristics of the dual sided aircraft light assembly will become apparent from the subsequent detailed description and the appended claims, taken in conjunction with the accompanying drawings and the preceding background.

DETAILED DESCRIPTION

Referring first toFIG.1, an example embodiment of an aircraft100is depicted. The depicted aircraft100includes a fuselage102having coupled thereto a pair of wings104(104-1,104-2), a pair of engines106(106-1,106-2), and landing gear108(108-1,108-2,108-3). It will be appreciated that various other aircraft assemblies and components may also be coupled to, and disposed within, the fuselage102. It will additionally be appreciated that although the depicted aircraft100is a turbojet aircraft, the present disclosure encompasses various other types of aircraft including, for example, rotor craft, helicopters, unmanned aerial vehicles, and the like.

The landing gear106, at least in the depicted embodiment, includes main landing gear108-1,108-2, and nose landing gear108-3, all of which are depicted in an extended position. As may be appreciated, at least for the depicted aircraft100, the landing gear may be selectively moved between the extended position and a retracted position. It will also be appreciated that in other embodiments the landing gear108may be fixed and/or it may include more or less than this number of landing gear arrangements.

No matter the number and configuration of the landing gear108, at least a portion of the landing gear108has at least one dual sided aircraft light assembly110coupled thereto. The aircraft100in the depicted embodiment has two light assemblies110coupled to each of the main landing gear108-1,108-2and to the nose landing gear108-3. It will be appreciated, however, that this is merely one example embodiment and that in other embodiments more or less than two light assemblies110may be coupled to each landing gear108and/or not all of the landing gear108of the aircraft100may one or more light assemblies110coupled thereto.

Turning now toFIGS.2and3, one embodiment of a dual sided aircraft light assembly110is depicted and will now be described. The depicted light assembly110includes a mount structure202, a plurality of first light emitters204, a plurality of first optics206, a plurality of second light emitters208, a plurality of second optics212, a first lens214, and a second lens216. The mount structure202is adapted to be mounted on the aircraft landing gear108. Indeed, inFIG.1it is mounted on the landing gear108. In the depicted embodiment, the mount structure202comprises a housing218within which a power supply circuit222is disposed.

The plurality of first light emitters204are coupled to the mount structure202via, for example, a suitable first printed circuit board (PCB) (not illustrated). Each of the first light emitters204is disposed such that, upon being electrically energized, it emits light in a first direction224. The first direction224, asFIG.2depicts, is at an acute angle (α) relative to a reference line226that extends in a reference direction228. Although the first light emitters204may be implemented using any one of numerous known light emitters, in the depicted embodiment each of the plurality of first light emitters204is a light emitting diode (LED).

The plurality of first optics206are disposed adjacent to the plurality of first light emitters204. In particular, each first optic206is associated with, and is disposed to receive the light emitted from, a different one of the first light emitters204. Thus, there is a single first optic206associated with each single first light emitter204. The first optics206may be implemented using any one of numerous known optics that are configured to focus the light emitted from the first light emitters204into a first light beam232that is directed in the first direction224.

The plurality of second light emitters208are coupled to the mount structure via, for example, a suitable second PCB (not illustrated). Each of the second light emitters is disposed such that, upon being energized, it emits light in a second direction234. The second direction234is at an obtuse angle (β) relative to the reference line226and the reference direction228. In the embodiment depicted inFIG.2, it is seen that the obtuse angle (β) is 180-degrees. Thus, the second direction234is parallel to the reference line226and is directly opposite the reference direction228. In the embodiment depicted inFIG.3, however, the obtuse angle (β) is less than 180-degrees. As with the first light emitters204, the second light emitters208may also be implemented using any one of numerous known light emitters; however, in the depicted embodiment each of the plurality of second light emitters208is also an LED.

The plurality of second optics212are disposed adjacent to the plurality of second light emitters208. In particular, each second optic212is associated with, and is disposed to receive the light emitted from, a different one of the second light emitters208. Thus, there is a single second optic212associated with each single second light emitter208. The second optics212may be implemented using any one of numerous known optics that are configured to focus the light emitted from the second light emitters208into a second light beam236that is directed in the second direction234.

The first lens214is coupled to, and encloses, the first light emitters204and the first optics206. Similarly, the second lens216is coupled to, and encloses the second light emitters208and the second optics212. The first and second lenses214,216primarily provide protection for the first and second light emitters204,208and the first and second optics206,212. However, in some embodiments the first and second lenses214,216may also further shape and/or focus the first and second light beams232,236, respectively.

As previously mentioned, in the embodiments depicted inFIGS.2and3, the mount structure202comprises the housing218. The housing218is structurally configured in a manner that causes the first light emitters204to emit light in the first direction224and the second light emitters208to emit light in the second direction234. In particular, the housing218includes a first mount surface238and a second mount surface242on which the first plurality of light emitters204and the second plurality of light emitters208are mounted, respectively. These mount surfaces238,242are configured such that the first and second light emitters204,208, when energized, will emit light in the first and second directions224,234, respectively.

As was also previously mentioned, the power supply222is disposed within the housing218. The power supply222is electrically coupled to the first light emitters204and the second light emitters208. The power supply222also is coupled to receive electrical power from the aircraft100and is configured to selectively energize the first light emitters204and/or the second light emitters208. That is, based on a command signal from, for example, the cockpit, the power supply222can energize either, or both, of the first and/or the second light emitters204,208.

In some embodiments, the configuration of the landing gear108may not make it possible to mount both the first and second light emitters204,208on the housing218. This may be due to space constraints or to avoid light blockage by the landing gear108. No matter the specific reason, for such configurations, the mount structure202comprises a plurality of brackets. More specifically, asFIG.4depicts, the mount structure202comprises a first bracket402and a second bracket404. The first bracket402is coupled to the plurality of first light emitters204, and more specifically to the housing218. The second bracket404is coupled to the plurality of second light emitters208. The second bracket404is also coupled to, and is spaced apart from, the first bracket402. In the depicted embodiment, a coupler406is used to couple the first and second brackets402,404together. AsFIG.4also depicts, a power line408electrically couples the power supply222to the second light emitters208.

It should be noted that in some embodiments, such as the embodiments depicted inFIGS.2and4, the second direction234is parallel to the reference line226and directly opposite the reference direction228. Moreover, in these embodiments the second plurality of lights208are symmetrically disposed relative to the reference line226. In other embodiments, such as the one depicted inFIG.5, the plurality of second light emitters208are asymmetrically disposed relative to the reference line226.

The aircraft light assembly disclosed herein can be mounted on the landing gear of an aircraft and can selectively provide illumination both forward and rearward of the aircraft. Thus, the light assembly can be used to provide illumination for landing, taxiing, and pushback operations.

As used herein, the term “axial” refers to a direction that is generally parallel to or coincident with an axis of rotation, axis of symmetry, or centerline of a component or components. For example, in a cylinder or disc with a centerline and generally circular ends or opposing faces, the “axial” direction may refer to the direction that generally extends in parallel to the centerline between the opposite ends or faces. In certain instances, the term “axial” may be utilized with respect to components that are not cylindrical (or otherwise radially symmetric). For example, the “axial” direction for a rectangular housing containing a rotating shaft may be viewed as a direction that is generally parallel to or coincident with the rotational axis of the shaft. Furthermore, the term “radially” as used herein may refer to a direction or a relationship of components with respect to a line extending outward from a shared centerline, axis, or similar reference, for example in a plane of a cylinder or disc that is perpendicular to the centerline or axis. In certain instances, components may be viewed as “radially” aligned even though one or both of the components may not be cylindrical (or otherwise radially symmetric). Furthermore, the terms “axial” and “radial” (and any derivatives) may encompass directional relationships that are other than precisely aligned with (e.g., oblique to) the true axial and radial dimensions, provided the relationship is predominantly in the respective nominal axial or radial direction. As used herein, the term “substantially” denotes within 5% to account for manufacturing tolerances. Also, as used herein, the term “about” denotes within 5% to account for manufacturing tolerances.