Patent Application
20200172265
This disclosure relates generally to aircraft lighting systems, and more particularly to wildlife deterrence systems.
Aircraft collisions with airborne wildlife (i.e., bird strikes), particularly during take-off and landing, are an increasingly common occurrence and present an appreciable risk of damage to aircraft components (e.g., aircraft engines). As modern aircraft have become increasingly quiet, the risk of bird strikes has increased. Quieter aircraft are more difficult for airborne wildlife to detect. As a result, avoidance by airborne wildlife is more difficult because the wildlife may have less time to clear the flight path of the oncoming aircraft.
According to an embodiment of the present disclosure, a lighting system for an aircraft includes at least one light mounted on at least one landing gear assembly of the aircraft. The at least one light is configured to emit ultraviolet light when the at least one landing gear assembly is in a lowered condition.
In the alternative or additionally thereto, in the foregoing embodiment, the at least one light emits the ultraviolet light at a predetermined wavelength and frequency.
In the alternative or additionally thereto, in the foregoing embodiment, the predetermined wavelength and frequency is an airborne wildlife deterrence wavelength and frequency.
In the alternative or additionally thereto, in the foregoing embodiment, the airborne wildlife deterrence wavelength and frequency is configured to deter at least one predetermined airborne species.
In the alternative or additionally thereto, in the foregoing embodiment, the at least one light emits the ultraviolet light during a take-off or landing operation.
In the alternative or additionally thereto, in the foregoing embodiment, the at least one light is configured to direct the ultraviolet light toward a flight path vector of the aircraft when the aircraft has a non-zero angle of attack.
In the alternative or additionally thereto, in the foregoing embodiment, the ultraviolet light emitted by the at least one light is unobstructed by the aircraft between the at least one light and the flight path vector.
In the alternative or additionally thereto, in the foregoing embodiment, the ultraviolet light emitted by the at least one light is non-visible to humans.
In the alternative or additionally thereto, in the foregoing embodiment, the at least one landing gear assembly is a plurality of landing gear assemblies. Each landing gear assembly of the plurality of landing gear assemblies includes the at least one light.
In the alternative or additionally thereto, in the foregoing embodiment, the at least one light of each landing gear assembly of the plurality of landing gear assemblies directs the ultraviolet light in a different direction than each other of the at least one light of each other landing gear assembly of the plurality of landing gear assemblies.
In the alternative or additionally thereto, in the foregoing embodiment, the at least one light is a plurality of lights. A first at least one light of the plurality of lights has a first predetermined wavelength and frequency configured to deter a first predetermined airborne wildlife species and a second at least one light of the plurality of lights has a second predetermined wavelength and frequency, different than the first predetermined wavelength and frequency, and configured to deter a second predetermined airborne wildlife species.
According to another embodiment of the present disclosure, a method for operating a lighting system for an aircraft is disclosed. An ultraviolet light is emitted with at least one light mounted on at least one landing gear assembly. The ultraviolet light is directed toward a flight path vector of the aircraft. The aircraft has a non-zero angle of attack. The ultraviolet light emitted by the at least one light is unobstructed by the aircraft between the at least one light and the flight path vector.
In the alternative or additionally thereto, in the foregoing embodiment, the at least one light emits the ultraviolet light during a take-off or landing operation.
In the alternative or additionally thereto, in the foregoing embodiment, the at least one light emits the ultraviolet light when the landing gear assembly is in a lowered condition.
According to another embodiment of the present disclosure, an aircraft includes at least one landing gear assembly and at least one light mounted on the at least one landing gear assembly. The at least one light is configured to emit ultraviolet light. The at least one light is configured to direct the ultraviolet light toward a flight path vector of the aircraft when the aircraft has a non-zero angle of attack.
In the alternative or additionally thereto, in the foregoing embodiment, the at least one light emits the ultraviolet light at a predetermined wavelength and frequency.
In the alternative or additionally thereto, in the foregoing embodiment, the landing gear assembly includes a plurality of landing gear assemblies. Each landing gear assembly of the plurality of landing gear assemblies includes at least one light.
In the alternative or additionally thereto, in the foregoing embodiment, the at least one light of each landing gear assembly of the plurality of landing gear assemblies directs the ultraviolet light in a different direction than each other of the at least one light of each other landing gear assembly of the plurality of landing gear assemblies.
In the alternative or additionally thereto, in the foregoing embodiment, the at least one light emits the ultraviolet light during a take-off or landing operation.
In the alternative or additionally thereto, in the foregoing embodiment, the ultraviolet light emitted by the at least one light is unobstructed by the aircraft between the at least one light and the flight path vector.
The present disclosure, and all its aspects, embodiments and advantages associated therewith will become more readily apparent in view of the detailed description provided below, including the accompanying drawings.
It is noted that various connections are set forth between elements in the following description and in the drawings. It is noted that these connections are general and, unless specified otherwise, may be direct or indirect and that this specification is not intended to be limiting in this respect. A coupling between two or more entities may refer to a direct connection or an indirect connection. An indirect connection may incorporate one or more intervening entities. It is further noted that various method or process steps for embodiments of the present disclosure are described in the following description and drawings. The description may present the method and/or process steps as a particular sequence. However, to the extent that the method or process does not rely on the particular order of steps set forth herein, the method or process should not be limited to the particular sequence of steps described. As one of ordinary skill in the art would appreciate, other sequences of steps may be possible. Therefore, the particular order of the steps set forth in the description should not be construed as a limitation.
Referring to
Referring to
Referring to
Visual capabilities of airborne wildlife (e.g., birds) may permit said airborne wildlife to visually perceive UV light 14 that would generally be non-visible to humans. Thus, by emitting and/or pulsing UV light 14, the visibility of an aircraft (e.g., aircraft 1000) may be increased with respect to airborne wildlife (i.e., the UV light 14 may alert the airborne wildlife to the presence of the approaching aircraft 1000). Increased visibility may provide the airborne wildlife greater opportunity to avoid collision with the aircraft 1000 by clearing the flight path vector 22 of the aircraft.
The at least one light 12 may emit UV light 14 having a predetermined wavelength and/or frequency. For example, the UV light 14 may have a predetermined wavelength and/or frequency corresponding to an airborne wildlife deterrence wavelength and/or frequency (i.e., the wavelength and/or frequency is selected for deterrence of airborne wildlife by, for example, achieving optimum visibility of the UV light 14 with respect to airborne wildlife). In some embodiments, the airborne wildlife deterrence wavelength and/or frequency may be configured to deter at least one predetermined airborne wildlife species (e.g., geese, gulls, etc.). For example, the wavelength and/or frequency of the UV light 14 may be selected for optimum visibility of the UV light 14 by the at least one airborne wildlife species, thereby improving deterrence of the at least one airborne wildlife species from the flight path vector 22 of the aircraft 1000.
Configuration of the predetermined wavelength and/or frequency (e.g., the airborne wildlife deterrence wavelength and/or frequency) to deter at least one predetermined airborne wildlife species may be desirable, for example, where a particular airborne wildlife species is known to operate in a particular area (e.g., in the vicinity of a destination airport). For further example, said configuration of the predetermined wavelength and/or frequency may be desirable based on altitude, for example, where bird strikes by a particular airborne wildlife species are more common at a particular altitude while bird strikes by a different particular airborne wildlife species are more common at a different altitude. Accordingly, the predetermined wavelength and/or frequency of the UV light 14 emitted by the at least one light 12 may be adjusted based on the particular species of airborne wildlife most likely to strike the aircraft 1000.
In some embodiments, the at least one landing gear assembly 10 may be a plurality of landing gear assemblies 10 with each landing gear assembly of the plurality of landing gear assemblies 10 including at least one light 12. The at least one light 12 of each landing gear assembly of the plurality of landing gear assemblies 10 may direct the UV light 14 in a same direction or a different direction than each other of the at least one light 12 of each other landing gear assembly of the plurality of landing gear assemblies 10 (see, e.g.,
In some embodiments, the at least one light 12 may be a plurality of lights 12. Each light of the plurality of lights 12 may be configured to emit UV light 14 having the same wavelength and/or frequency. In some embodiments, a first at least one light of the plurality of lights 12 may emit UV light 14 having a first wavelength and/or frequency while a second at least one light of the plurality of lights 12 may emit UV light 14 having a second wavelength and/or frequency, different than the first wavelength and/or frequency. In some embodiments, the first wavelength and/or frequency may be configured to deter a first at least one predetermined airborne wildlife species while the second wavelength and/or frequency may be configured to deter a second at least one predetermined airborne wildlife species.
Shadowing (i.e., obstruction) of the UV light 14 by the aircraft 1000, between the at least one light 12 and the flight path vector 22, may reduce the effectiveness of the UV light 14 in deterring airborne wildlife. For example, depending on the location of the at least one light 12 with respect to the aircraft 1000, components of the aircraft 1000 (e.g., the fuselage 1002 or the engines 1006) may obstruct some or all of the UV light from reaching the flight path vector 22. The location of the at least one light 12 on the at least one landing gear assembly 10 may reduce or prevent shadowing effects of the aircraft 1000 by providing a more direct line-of-sight between the at least one light 12 and the flight path vector 22 with respect to potentially obstructing surfaces of the aircraft 1000. Shadowing of the UV light 14 may be further reduced by directing the UV light 14 toward the flight path vector 22 of the aircraft 1000 when the aircraft has a non-zero angle of attack 24. For example, the UV light 14 emitted by the at least one light 12 may be partially or completely unobstructed by the aircraft 1000 between the at least one light 12 and the flight path vector 22.
In some embodiments, the at least one light 12 may be activated or deactivated manually (e.g., by a pilot). For example, the at least one light 12 may be activated when the aircraft 1000 is proceeding to lower altitudes (e.g., below 3,000 meters), where the majority of bird strikes occur. Alternatively, in some embodiments, the at least one light 12 may be activated or deactivated automatically (e.g., by a control system) when the landing gear assembly 10 is in a lowered condition.
While various aspects of the present disclosure have been disclosed, it will be apparent to those of ordinary skill in the art that many more embodiments and implementations are possible within the scope of the present disclosure. For example, the present disclosure as described herein includes several aspects and embodiments that include particular features. Although these particular features may be described individually, it is within the scope of the present disclosure that some or all of these features may be combined with any one of the aspects and remain within the scope of the present disclosure. Accordingly, the present disclosure is not to be restricted except in light of the attached claims and their equivalents.
