EXTERIOR AIRCRAFT LIGHT COVER, EXTERIOR AIRCRAFT LIGHT COMPRISING THE SAME, AND METHOD OF UPGRADING OR MAINTAINING AN EXTERIOR AIRCRAFT LIGHT

Abstract

An exterior aircraft light cover with integrated illumination includes a mounting portion, configured to be mounted to an exterior aircraft light housing; a light transmissive pane, supported by the mounting portion. The mounting portion and the light transmissive pane are configured to jointly close the exterior aircraft light housing. The cover also includes at least one photovoltaic device, which is configured for generating electric energy when illuminated; at least one electric storage device, which is configured for storing the electric energy generated by the at least one photovoltaic device; and at least one ancillary light source, which is operable with electric energy supplied by at least one of the at least one photovoltaic device and the at least one electric storage device.

Claims

1. An exterior aircraft light cover with integrated illumination, comprising: a mounting portion, configured to be mounted to an exterior aircraft light housing; a light transmissive pane, supported by the mounting portion, wherein the mounting portion and the light transmissive pane are configured to jointly close the exterior aircraft light housing; at least one photovoltaic device, which is configured for generating electric energy when illuminated; at least one electric storage device, which is configured for storing at least a portion of the electric energy generated by the at least one photovoltaic device; and at least one ancillary light source, which is operable with electric energy supplied by at least one of the at least one photovoltaic device and the at least one electric storage device.

2. The exterior aircraft light cover according to claim 1, wherein the exterior aircraft light housing is a dedicated component or a recess formed in a body of an aircraft.

3. The exterior aircraft light cover according to claim 1, further comprising: a controller configured for switching \or dimming the at least one ancillary light source, wherein the controller is configured for switching or dimming the at least one ancillary light source in response to a sensor signal received by the controller.

4. The exterior aircraft light cover according to claim 3, further comprising: a sensor that is one of a light sensor, a variometer or an accelerometer, wherein the sensor is configured for supplying a sensor signal to the controller.

5. The exterior aircraft light cover according to claim 4, comprising at least one first photovoltaic device and at least one second photovoltaic device, wherein the controller is configured for switching and/or dimming the at least one ancillary light source in response to the electric power provided by the at least one first photovoltaic device and the at least one second photovoltaic device, in particular in response to a difference between the electric power provided by the at least one first photovoltaic device and the at least one second photovoltaic device.

6. The exterior aircraft light cover according to claim 5, wherein the controller is configured for switching the at least one ancillary light source on if the at least one first photovoltaic device provides more electric power than the at least one second photovoltaic device, and/or wherein the controller is configured for switching the at least one ancillary light source off if the at least one first photovoltaic device provides less electric power than the at least one second photovoltaic device.

7. The exterior aircraft light cover according to claim 1, wherein the at least one ancillary light source is supported by at least one of the mounting portion and the light transmissive pane.

8. The exterior aircraft light cover according to claim 1, wherein the at least one ancillary light source is arranged at a periphery of the light transmissive pane, wherein the at least one ancillary light source in particular includes a light strip that extends at least along a portion of the periphery of the light transmissive pane.

9. The exterior aircraft light cover according to claim 1, further comprising a support structure, supporting at least one of the at least one photovoltaic device, the at least one electric storage device and the controller.

10. The exterior aircraft light cover according to claim 9, wherein the support structure includes a hood extending over a portion of the light transmissive pane, wherein the hood is in particular spaced apart from the light transmissive pane.

11. The exterior aircraft light cover according to claim 1, wherein the at least one electric storage device includes at least one supercapacitor.

12. An exterior aircraft light, comprising: an exterior aircraft light housing; at least one targeted light source, supported by the exterior aircraft light housing; and an exterior aircraft light cover according to any of the preceding claims.

13. An exterior aircraft light according to claim 12, wherein the exterior aircraft light is configured to selectively operate as a landing light or as a take-off light, wherein the exterior aircraft light cover is configured to detect at least a portion of the light emitted by the exterior aircraft light in order to switch on the at least one ancillary light source when the exterior aircraft light is operating as a landing light, and to switch off the at least one ancillary light source when the exterior aircraft light is operating as a take-off light.

14. An aircraft comprising at least one exterior aircraft light according to claim 12.

15. A method of upgrading or maintaining an exterior aircraft light comprising an exterior aircraft light cover having a light transmissive pane, wherein the method includes: removing the exterior aircraft light cover from the exterior aircraft light; and mounting an exterior aircraft light cover according to claim 1 to the exterior aircraft light.

Description

DETAILED DESCRIPTION

[0058] FIG. 1 depicts a schematic front view of an aircraft 100, in particular an air plane 100, comprising a fuselage 102, two wings 104, laterally extending from opposite sides of the fuselage 102, and two engines 106. Each of the engines 106 is mounted to one of the wings 104. The skilled person understands that the aircraft 100 may comprise more than two engines 106, in particular four engines 106.

[0059] A tailplane 108 and a vertical stabilizer 110 extend from an upper rear portion of the fuselage 102. The aircraft 100 further comprises a front gear 112 and a main gear 114, extending from the bottom of the fuselage 102 and supporting the aircraft 100 on the ground 116.

[0060] The aircraft 100 comprises a plurality of exterior aircraft lights 2, such as take-off lights, landing lights, taxi lights, navigation lights and anti-collision lights.

[0061] Exterior aircraft lights 2 may be provided at the gears 112, 114, in particular the front gear 112, at the fuselage 102, at the wings 104, at the tailplane 108 and/or at the vertical stabilizer 110 of the aircraft 100. Exterior aircraft lights 2 in particular may be mounted at or next to the wing roots 118, i.e. to the portions 118 of the aircraft 100 at which the wings 104 extend from the fuselage 102.

[0062] The positions of the exterior aircraft lights 2 depicted in FIG. 1 are only exemplary. The positions may vary depending on the type of the aircraft 100 as well as on the type of the respective exterior aircraft light 2.

[0063] Each of the exterior aircraft lights 2 comprises a housing 3. The housing 3 may be a dedicated component mounted to the aircraft 100. The housing 3 also may be provided as an opening or recess formed within the outer surface of the aircraft 100.

[0064] FIG. 2 depicts an exterior aircraft light 2 according to an exemplary embodiment of the invention, comprising an exterior aircraft light cover 10 according to an embodiment of the invention. The exterior aircraft light 2 is mounted to the aircraft 100, in particular to an exterior surface of the aircraft 100. In the embodiment depicted in FIG. 2, the housing 3 of the exterior aircraft light 2 is provided as an opening or recess formed within the outer surface of the aircraft 100

[0065] The exterior aircraft light 2, depicted in FIG. 2, is a multi functional runway light (“MFRL”), combining at least the functions of a take-off light and a landing light. The MFRL may further include the functions of a runway turn-off light and/or a taxi light.

[0066] The exterior aircraft light 2, depicted in FIG. 2, includes first targeted light sources 4, which, when operated, provide the functionality of a landing light, and second targeted light sources 6, which, when operated, provide the functionality of a take-off light. Thus, when the aircraft 100 is approaching the ground 116 for landing, the first targeted light sources 4 (“landing light sources 4”) are switched on, and the second targeted light sources 6 (“take-off light sources 6”) are switched off. In contrast, the first targeted light sources 4 (“landing light sources 4”) are switched off and the second targeted light sources 6 (“take-off light sources 6”) are switched on for take-off

[0067] Although not explicitly shown in the figures, the exterior aircraft light 2 may further comprise additional targeted light sources, in order to allow operating the exterior aircraft light 2 as at least one of a runway turn-off light and a taxi light.

[0068] The exterior aircraft light cover 10 is mounted in front of the targeted light sources 4, 6. In other words, the exterior aircraft light cover 10 is arranged between the targeted light sources 4, 6 and the exterior environment of the aircraft 100.

[0069] Although the exterior aircraft light 2, depicted in FIG. 2, is a multi functional runway light (“MFRL”), the skilled person understands that an exterior aircraft light cover 10 according to exemplary embodiments of the invention may be employed in combination with other types of exterior aircraft lights 2 as well.

[0070] An exterior aircraft light cover 10 according to exemplary embodiments of the invention in particular may be employed in combination with exterior aircraft lights 2 providing only one function, e.g. the function of a take-off light, the function of a landing light, the function of a runway turn-off light or the function of a taxi light, respectively. It may also be employed in combination with exterior aircraft lights having more functions than the described MFRL.

[0071] The exterior aircraft light cover 10 comprises a mounting portion 12, extending along an outer periphery of the exterior aircraft light cover 10. The mounting portion 12 is configured to be mounted to the aircraft 100. The mounting portion 12 in particular is configured to be mounted to a housing 3 of an exterior aircraft light 2 (“exterior aircraft light housing 3”), e.g. by means of screws or bolts 14, extending through the mounting portion 12.

[0072] The exterior aircraft light cover 10 further comprises a light transmissive pane 16, supported by the mounting portion 12. The light transmissive pane 16 allows light, which is emitted by the targeted light sources 4, 6 of the exterior aircraft light 2, to pass through the exterior aircraft light cover 10.

[0073] The mounting portion 12 extends along the outer periphery of the light transmissive pane 16 and acts as a support portion/retainer, supporting the light transmissive pane 16.

[0074] In a first configuration, which is depicted in FIG. 2, the light transmissive pane 16 may be transmissive to light over substantially its whole spatial extension. In alternative configurations, which are not explicitly depicted in the figures, the light transmissive pane 16 may comprise light transmissive portions and opaque portions, which are not light transmissive. The light transmissive pane 16 may further comprise one or more colored light transmissive portions, in order to facilitate emitting an at least partially colored light distribution.

[0075] The light transmissive pane 16 or the light transmissive portions of the transmissive pane 16 may be at least partially transparent, in particular substantially fully transparent.

[0076] When mounted to the exterior surface of the aircraft 100, the light transmissive pane 16 and the mounting portion 12 jointly close the exterior aircraft light housing 3 on its outside, i.e. on the side facing the outside of the aircraft 100. As a result, the light transmissive pane 16 protects the targeted light sources 4, 6 from adverse ambient influences, such as mechanical impact, dirt, water, moisture, etc.

[0077] In the embodiment depicted in the figures, the light transmissive pane 16 has a basically trapezoidal contour with rounded edges. The contour of the light transmissive pane 16 depicted in the figures, however, is only exemplary and not limiting. The skilled person understands that other shapes of the contour of the light transmissive pane 16, as long as they are suitable for the desired functionality of the respective exterior aircraft light 2, are possible as well.

[0078] The exterior aircraft light cover 10 further comprises at least one ancillary light source 18, 20. The at least one ancillary light source 18, 20 may be mounted to and/or supported by the mounting portion 12 and/or to the light transmissive pane 16. In the non-limiting embodiment depicted in FIG. 2, an ancillary light source 18 is provided as a light strip 18 extending along the inner rim of the mounting portion 12, i.e. along the inner edge of the mounting portion 12 supporting the light transmissive pane 16.

[0079] The light emitted by the at least one ancillary light source 18, 20 does not significantly contribute or not contribute at all to the intended functionality of the exterior aircraft light 2, i.e. to the functionality of the exterior aircraft light 2 as a landing light and/or take-off light and/or runway turn-off light and/or taxi light. Instead, the desired functionality of the exterior aircraft light 2 is realized entirely or substantially entirely by the light emitted by the targeted light sources 4, 6 of the exterior aircraft light 2. In other words, the light emission from the targeted light sources 4, 6 is sufficient for satisfying the requirements of the intended functionality of the exterior aircraft light 2.

[0080] In the embodiment depicted in FIG. 2, the light strip constituting an ancillary light source 18 extends along three of the four sides of the trapezoidal shape of the light transmissive pane 16. This configuration of the ancillary light source 18, however, is only exemplary. In other embodiments of the present invention, which are not depicted in the figures, the at least one ancillary light source 18 may have a different configuration. The at least one ancillary light source 18 in particular may extend along a smaller or along a larger portion, in particular along fewer or more sides, of the outer periphery of the exterior aircraft light cover 10.

[0081] Additional ancillary light sources 20 may be provided on the inner side of the light transmissive pane 16, i.e. on the side of the light transmissive pane 16 facing the targeted light sources 4, 6 of the exterior aircraft light 2.

[0082] The ancillary light sources 18, 20 may include LEDs and/or other types of electrical light sources. The ancillary light sources 18, 20 may further include optical elements (not shown), such as lenses, prisms, reflectors etc., which are configured for shaping the light distribution emitted by the ancillary light sources 18, 20 into a desired pattern.

[0083] All ancillary light sources 18, 20 may be configured for emitting light having the same color. Alternatively, different ancillary light sources 18, 20 may be configured for emitting light of different colors. In particular, ancillary light sources 18, 20 of different colors may be employed at different exterior aircraft lights 2 of the aircraft 100, in order to help ground personnel to easily and reliably distinguish between the different exterior aircraft lights 2 based on the different colors of the light emitted by the respective ancillary light sources 18, 20.

[0084] FIG. 3 depicts an exterior aircraft light cover 10 according to an exemplary embodiment of the invention in a configuration, in which it is separated/de-mounted from the exterior aircraft light 2. In consequence, the targeted light sources 4, 6, which are part of the exterior aircraft light 2, but do not belong to the exterior aircraft light cover 10, are not shown in FIG. 3.

[0085] In FIG. 3, the exterior aircraft light cover 10 is depicted from the side facing the interior of the aircraft 100, when the exterior aircraft light cover 10 is mounted to an exterior aircraft light 2. In other words, when compared to FIG. 2, the exterior aircraft light cover 10 is shown from the opposite side in FIG. 3.

[0086] In FIG. 3, the exterior aircraft light cover 10 is oriented such that the targeted light sources 4, 6 of the exterior aircraft light 2 are located on the right side of FIG. 3, when the exterior aircraft light cover 10 is mounted to an exterior aircraft light housing.

[0087] A hood 22 is provided at the left side of the exterior aircraft light cover 10, i.e. at the side of the exterior aircraft light cover 10 located opposite the targeted light sources 4, 6 of the exterior aircraft light 2, when the exterior aircraft light cover 10 is mounted to the exterior aircraft light 2.

[0088] The hood 22 is mounted to and supported by the mounting portion/retainer 12 of the exterior aircraft light cover 10. The hood 22, which in particular may be made from a non-transparent material, comprises an inclined plane 24, which is arranged at an arcuate angle with respect to the plane of the light transmissive pane 16. In alternative embodiments, which are not depicted in the figures, the plane 24 may be arranged substantially parallel to the plane of the light transmissive pane 16.

[0089] The hood 22 also comprises two side portions 25, extending between the inclined plane 24 and the mounting portion 12 and supporting the inclined plane 24.

[0090] The plane 24 is arranged in some distance from the light transmissive pane 16, forming a free space between the plane 24 and the light transmissive pane 16.

[0091] The free space defined by the hood 22 and the light transmissive pane 16 is open at the side facing the targeted light sources 4, 6 of the exterior aircraft light 2 (cf. FIG. 2), in order to allow light, which is emitted from said targeted light sources 4, 6, to enter into the free space and to pass through the portion of the light transmissive pane 16 located under the hood 22.

[0092] FIG. 4 depicts the exterior aircraft light cover 10, shown in FIG. 3, from the opposite side, i.e. from the side facing the outside of the aircraft, when the exterior aircraft light cover 10 is mounted to an exterior aircraft light 2/to an aircraft 100 (cf. FIG. 2).

[0093] FIG. 4 shows a plurality of electric components 26, 28, 30, 32, 34, mounted to the side of the inclined plane 24 of the hood 22 facing the light transmissive pane 16.

[0094] The electric components 26, 28, 30, 32, 34 mounted to the hood 22 include at least one photovoltaic device 26, 28, e.g. a solar cell, in particular a plurality of photovoltaic devices 26, 28. The at least one photovoltaic device 26, 28 is arranged at a position at which it is illuminated by the light emitted from the targeted light sources 4, 6 of the exterior aircraft light 2 and reflected, in particular due to Fresnel reflections, by the light transmissive pane 16 towards the at least one photovoltaic device 26, 28.

[0095] It is noted that for simplicity, the hood 22 and the electric components 26, 28, 30, 32, 34 are not depicted in FIG. 2.

[0096] FIG. 5 shows a block diagram of an electric circuit 33, comprising the electric components 26, 28, 30, 32, 34 of the exterior aircraft light cover 10.

[0097] The plurality of photovoltaic devices 26, 28 include at least one first photovoltaic device 26, which is arranged at locations predominantly illuminated by light emitted by the landing light sources 4, and at least one second photovoltaic device 28, which is arranged at locations predominantly illuminated by light emitted by the take-off light sources 6.

[0098] The electric components 26, 28, 30, 32, 34, mounted to the hood 22, further comprise at least one electric storage device 30, for example at least one supercapacitor 30. The at least one electric storage device 30 is configured for storing at least a portion of the electric energy generated by the at least one photovoltaic device 26, 28 and selectively supplying said electric energy to the at least one ancillary light source 18, 20 for operating said at least one ancillary light source 18, 20. The at least one electric storage device 30 may in particular be configured to allow operating the at least one ancillary light source 18, 20 of the exterior aircraft light cover 10 for up to two hours, without the at least one photovoltaic device 26, 28 being illuminated.

[0099] The electric components 26, 28, 30, 32, 34 also include a controller 34, configured for switching and/or dimming the at least one ancillary light source 18, 20.

[0100] The controller 34 is electrically coupled to the photovoltaic devices 26, 28, the at least one electric storage device 30, the at least one ancillary light source 18, 20, and an (optional) sensor 32.

[0101] The controller 34 is configured for controlling the flow of electric energy between the photovoltaic devices 26, 28, the at least one electric storage device 30 and the at least one ancillary light source 18, 20.

[0102] The sensor 32 may comprise a variometer and/or an accelerometer, which is configured for detecting the height and/or the acceleration of the aircraft 100.

[0103] The sensor 32 and the controller 34 are operated with electric energy supplied by the photovoltaic devices 26, 28 and/or the at least one electric storage device 30 as well.

[0104] In the embodiment depicted in FIG. 4, the electric storage devices 30, the sensor 32 and the controller 34 are arranged on the side of the inclined plane 24 facing the light transmissive pane 16. The electric storage devices 30, the sensor 32 and/or the controller 34 may alternatively be mounted to the opposite side of the inclined plane 24, i.e. the side facing away from the light transmissive pane 16.

[0105] An exterior aircraft light cover 10 according to an exemplary embodiment, as it is depicted in FIGS. 2 to 5, is an exterior aircraft light cover 10 that allows for providing additional illumination of an exterior aircraft light 2.

[0106] The exterior aircraft light cover 10 is in particular operable, without establishing any electric connections between the exterior aircraft light cover 10 and the electric system of the aircraft 100. In consequence, a conventional transparent pane, covering the light sources of a conventional exterior aircraft light, may be replaced easily by an exterior aircraft light cover 10 according to an exemplary embodiment of the invention, without intervening with the electric system of the aircraft 100. As an exterior aircraft light cover 10 according to an exemplary embodiment of the invention does not intervene with the electric system of the aircraft 100, the process of certifying such an exterior aircraft light cover 10 for use in commercial aircraft is considerably simplified.

[0107] In the following, different possible modes of operating an exterior aircraft light cover 10 according to exemplary embodiments of the invention are described. In an exterior aircraft light cover 10 according to exemplary embodiments of the invention, one or more of these modes may be implemented.

[0108] For example, it may be desirable that the ancillary light sources 18, 20 of the exterior aircraft light cover 10 are switched on, when the aircraft 100 is approaching an airport, landing, and/or taxiing at said airport, and it may be desirable that the ancillary light sources 18, 20 of the exterior aircraft light cover 10 are switched off for take-off

[0109] According to an exemplary embodiment of the invention, an automatic switching of the ancillary light sources 18, 20 for take-off and landing may be implemented by configuring the controller 34 to evaluate signals provided by a sensor 32. Said sensor 32 may in particular include a variometer and/or an accelerometer.

[0110] Based on a sensor signal provided by a variometer, the controller 34 is capable to determine whether the aircraft 100 is descending for landing and to switch on the ancillary light sources 18, 20 of the exterior aircraft light cover 10, when such a landing situation is detected.

[0111] From the signals provided by a variometer, the controller 34 is further capable to determine whether the aircraft 100 is ascending during take-off and to switch on the ancillary light sources 18, 20, when such a take-off situation is detected.

[0112] Alternatively or additionally, an accelerometer may be used for detecting whether the aircraft is in a take-off situation or in a landing situation.

[0113] For example, a sensor signal from an accelerometer, corresponding to a strong acceleration that extends at least over a predetermined amount of time, indicates that the aircraft 100 is taking-off, and a sensor signal, corresponding to a deceleration that extends at least over a predetermined amount of time, indicates that the aircraft 100 is in a landing approach.

[0114] Switching the ancillary light sources 18, 20 of the exterior aircraft light cover 10 based on signals provided by such a sensor 32 allows for a reliable switching of the ancillary light sources 18, 20 on and off, in particular in situations in which the operational state of the exterior aircraft light 2, to which the exterior aircraft light cover 10 is mounted, does not indicate whether the aircraft 100 is currently taking-off or landing.

[0115] When the mode of operation of the exterior aircraft light 2 indicates whether the aircraft 100 is currently taking-off or landing, the light emitted by the targeted light sources 4, 6 of the exterior aircraft light 2 may be used as an indicator for determining whether the ancillary light sources 18, 20 of the exterior aircraft light cover 10 are to be switched on or off

[0116] In the following, a method of using the light emitted by the targeted light sources 4, 6 of the exterior aircraft light 2 as an indicator for determining whether the ancillary light sources 18, 20 of the exterior aircraft light cover 10 are to be switched on or off is described with reference to FIGS. 6 and 7. FIGS. 6 and 7 show the exterior aircraft light 2, depicted in FIG. 2, in different operational states.

[0117] FIG. 6 illustrates the operation of the exterior aircraft light 2 in a landing situation, in which the landing light sources 4 are switched on, and the take-off light sources 6 are switched off. FIG. 6 shows that in a landing situation, in which the landing light sources 4 are switched on, more light is reflected by the light transmissive pane 16 onto the first photovoltaic device 26 than onto the second photovoltaic device 28.

[0118] FIG. 7 illustrates the operation of the exterior aircraft light 2 during take-off. During take-off, the landing light sources 4 are switched off, and the take-off light sources 6 are switched on. FIG. 7 shows that during take-off, when the take-off light sources 6 are switched on, more light is reflected by the light transmissive pane 16 onto the second photovoltaic device 28 than onto the first photovoltaic device 26.

[0119] In a configuration as it is depicted in FIGS. 6 and 7, the photovoltaic devices 26, 28 are not only configured to be used as energy generating components for providing the electric energy, which is used for operating various components of the exterior aircraft light cover 10. The photovoltaic devices 26, 28 are additionally employed as light detectors for detecting the operational states of the landing light sources 4 and the take-off light sources 6, respectively. As the landing light sources 4 and the take-off light sources 6 are not switched on simultaneously, detecting the operational states of the landing light sources 4 and the take-off light sources 6 may in particular include comparing the energies/voltages, supplied by the first and second photovoltaic devices 26, 28, with each other.

[0120] By comparing the electric energies/voltages, supplied by the first and second photovoltaic devices 26, 28, with each other, the controller 34 may determine that only the landing light sources 4 are switched on. This indicates that the aircraft 100 is currently in a landing approach. In consequence, the controller 34 activates the ancillary light sources 18, 20 of the exterior aircraft light cover 10.

[0121] Similarly, by comparing the energies/voltages, supplied by the first and second photovoltaic devices 26, 28, with each other, the controller 34 may determine that only the take-off light sources 6 are switched on. This indicates that the aircraft 100 is preparing for take-off. In consequence, the ancillary light sources 18, 20 of the exterior aircraft light cover 10 are switched off by the controller 34.

[0122] In an embodiment, in which the ancillary light sources 18, 20 of the exterior aircraft light cover 10 are switched on and off based on detected light, emitted by the landing light sources 4 and the take-off light sources 6 of the exterior aircraft light 2 and then reflected by the light transmissive pane 16 towards the photovoltaic devices 26, 28, the additional sensor 32, such as a variometer or an accelerometer, may be saved. This may allow for reducing the complexity and/or cost of the exterior aircraft light cover 10.

[0123] While the invention has been described with reference to exemplary embodiments, it will be understood by those skilled in the art that various changes may be made and equivalence may be substituted for elements thereof without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teaching of the invention without departing from the essential scope thereof Therefore, it is intended that the invention not be limited to the particular embodiments disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.