Aircraft beacon light and aircraft including an aircraft beacon light

Abstract

An aircraft beacon light (2) for mounting to an aircraft fuselage (104), comprising: a support structure (4) having a carrier (40) and a guide rod (42), the guide rod being used to support the carrier (40) and to space the carrier (40) from the aircraft fuselage (104); and a lighting system (6) supported by the support structure (4), the lighting system (6) having a plurality of light sources (60), a light optic (62) for redirecting at least a portion of light emitted by the plurality of light sources (60), and a lens cover (68), wherein the plurality of light sources (60) and the light optic (62) are arranged between the carrier (40) and the lens cover (68); wherein the aircraft beacon light (2) is configured to emit a red flashing beacon light output during operation.

Description

Technical Field

[0001] The present invention relates to external aircraft lighting, and more particularly to an aircraft beacon light and an aircraft equipped with the aircraft beacon light. Background Art

[0002] Almost all aircraft are equipped with external lighting systems. For example, large commercial aircraft have many different external lights. An exemplary set of external aircraft lights are passive visible lights, such as navigation lights, white flashing anti-collision lights, and red flashing beacon lights. Common aircraft have two red flashing beacon lights arranged on the top of the aircraft fuselage and on the bottom of the aircraft fuselage, respectively. Their red flashing lights at least indicate that the aircraft's engines are started. Another exemplary set of external aircraft lights are headlights that allow pilots to view the area in front of them when they are sitting in the cockpit, such as taxi lights, take-off lights, landing lights, and runway corner lights. Another example of external aircraft lights are scanning lights that allow aircraft structures to be inspected in the dark, such as wing scanning lights. In the case of a large number of external aircraft lights, an external aircraft lighting system that has little impact on aircraft design / performance is beneficial.

[0003] It would therefore be beneficial to provide external aircraft lights that achieve good lighting effectiveness and have little impact on aircraft operation. Summary of the invention

[0004] An exemplary embodiment of the present invention includes an aircraft beacon light for mounting to an aircraft fuselage, comprising: a support structure, the support structure including a carrier and a guide rod, the guide rod being used to support the carrier and to space the carrier from the aircraft fuselage; and a lighting system, the lighting system being supported by the support structure, the lighting system including a plurality of light sources, a light optic for redirecting at least a portion of light emitted by the plurality of light sources, and a lens cover, wherein the plurality of light sources and the light optic are arranged between the carrier and the lens cover; wherein the aircraft beacon light is configured to emit a red flashing beacon light output during operation.

[0005] Exemplary embodiments of the present invention allow for advantageous positioning of a lighting system of an aircraft beacon light relative to an aircraft fuselage, and therefore allow for highly unobstructed beacon light output while having a low aerodynamic impact on the aircraft. In the case where a guide rod spaces the lighting system from the aircraft fuselage, it is possible for the aircraft beacon light to emit a red flashing beacon light output in a direction that was not possible with previous methods where the lighting system was mounted directly to the aircraft fuselage. Moreover, in the case where the support structure has a guide rod and a carrier, the spacing of the lighting system from the aircraft fuselage can be performed in a manner that has a low impact on the aerodynamics of the aircraft. The term guide rod refers to a support element having a smaller cross-section than the carrier, so that the spacing between the aircraft fuselage and the carrier can be achieved without adding a large amount of aerodynamic drag to the aircraft. The guide rod and the carrier can form a mushroom type structure. The carrier can provide sufficient base area for carrying an extended lighting system, while the guide rod can support the lighting system in an aerodynamically efficient manner. The aerodynamic impact of the aircraft beacon light can be kept within acceptable limits while an optically beneficial position of the lighting system of the aircraft beacon light can be achieved.

[0006] When the aircraft beacon light is mounted to the aircraft fuselage, the guide rod spaces the carrier from the aircraft fuselage. The guide rod thus spaces the lighting system from the aircraft fuselage. When the aircraft beacon light is mounted to the aircraft fuselage, the plurality of light sources, the light optics and the lens cover are spaced from the aircraft fuselage. The lens cover does not surround the guide rod relative to the aircraft fuselage. The guide rod is an external element of the aircraft beacon light.

[0007] The guide rod supports the carrier and spaces the carrier from the aircraft fuselage. The guide rod has a proximal side facing the aircraft fuselage, and a distal side to which the carrier is attached. The guide rod can be considered as a column or a support for the carrier. The carrier protrudes beyond the distal side of the guide rod in a transverse direction. In other words, the carrier is a structure that extends further than the guide rod in a plane parallel to the part of the aircraft fuselage to which the aircraft beacon light is mounted. The guide rod and the carrier can be formed integrally. It is also possible that the guide rod and the carrier are initially separate components that are attached to each other.

[0008] A plurality of light sources and light optics are arranged between the carrier and the lens cover. The lens cover is arranged above the plurality of light sources and light optics to allow light from the plurality of light sources to pass through the plurality of light sources and light optics and to protect the plurality of light sources and light optics from hazardous aircraft environments, such as aerodynamic forces and impact particles during flight. The plurality of light sources and light optics are enclosed relative to the carrier by the lens cover. The lens structure may be a transparent or translucent structure through which light from the plurality of light sources passes.

[0009] The aircraft beacon light is configured to emit a red flash beacon light output during operation. In other words, the aircraft beacon light is configured to emit a flash of red light during operation. The flash of red light contributes to the beacon light functionality of the aircraft. The multiple light sources can be multiple red light sources, such as red LEDs. In this way, red light is produced, and the light optics and the lens cover can be free of color filters. It is also possible that the light optics and / or the lens cover include red color filters. In this case, the multiple light sources can be (for example) white light sources, wherein the downstream color filter provides a red light output. The term red light output covers any kind of light with a reddish hue. The red light output can be an aviation red light output according to Federal Aviation Regulations (FAR) Section 25.1397.

[0010] The aircraft beacon light is configured to emit a red flashing beacon light output during operation. The beacon light output can be in accordance with Federal Aviation Regulations (FAR) Section 25.1401. Specifically, the beacon light output in at least a hemisphere above or below the horizontal plane can meet the light intensity requirements of Federal Aviation Regulations (FAR) Section 25.1401. In other words, the beacon light output can meet at least the upper half or lower half of the light intensity requirements. The beacon light output can be achieved jointly by multiple light sources and light optics, or by multiple light sources, light optics, and lens covers. The lens cover may have an effective effect on shaping the beacon light output, or may substantially pass the light output shaped by the light optics.

[0011] The aircraft beacon light is configured to emit flashes of red light in operation. This wording relates to the perception of light output by an observer. For example, personnel at an airport would see flashes of red light emitted by an aircraft beacon light when they are within the output range of the aircraft beacon light.

[0012] The aircraft beacon light is configured to emit flashes of red light in operation. Specifically, the aircraft beacon light may have a controller that selectively provides power to a plurality of light sources, thereby intermittently illuminating the plurality of light sources, which in turn provide the emission of flashes of red light by the aircraft beacon light in operation. The controller may be coupled to an aircraft onboard power supply network on the one hand, and to the plurality of light sources on the other hand.

[0013] The lighting system includes a plurality of light sources. The plurality of light sources may include a plurality of LEDs. In certain embodiments, the plurality of light sources may include a plurality of red LEDs and / or a plurality of infrared LEDs. In this way, the aircraft beacon light may be well suited for use cases that rely on visible light and / or for covert operations.

[0014] The lighting system includes a lamp optic for redirecting at least a portion of light emitted by a plurality of light sources. The lamp optic may include one or more lenses, one or more reflectors, and / or one or more shutters. In certain embodiments, the lamp optic may include one or more lenses and may be free of metal reflectors and shutters.

[0015] According to another embodiment, the carrier has a cross-sectional carrier extension and the guide rod has a cross-sectional guide rod extension, and the cross-sectional carrier extension is between 5 and 40 times, specifically between 10 and 30 times, more specifically between 15 and 25 times, larger than the cross-sectional guide rod extension. In this way, a spacing between the carrier and the aircraft fuselage is provided in a particularly aerodynamically efficient manner. For a given carrier extension capable of supporting a given lighting system, the guide rod size is relatively small, thereby having a lower aerodynamic impact. In order to compare the cross-sectional carrier extension and the cross-sectional guide rod extension, the area within the periphery of the carrier and the guide rod can be viewed. In particular, the periphery with the largest cross-sectional extension in a plane parallel to that part of the aircraft fuselage to which the aircraft beacon light is mounted can be considered in that cross section of the carrier. For the guide rod, the extension in the cross-sectional plane parallel to the aircraft fuselage and in the middle between the carrier and the aircraft fuselage can be viewed. The guide rod can be a solid structure or a hollow structure. Regardless of whether the guide rod is solid or hollow, look at its outer extension to compare the cross-sectional carrier extension and the cross-sectional guide rod extension.

[0016] According to another embodiment, the guide rod has an elongated shape. Specifically, the guide rod may have an elongated shape between the front end and the rear end. The guide rod may have a rib shape, thereby supporting the carrier in an extended manner and having a smaller front surface area.

[0017] According to another embodiment, the guide rod has a guide rod length and a guide rod width, and the guide rod length is between 3 and 15 times, specifically between 5 and 12 times, more specifically between 8 and 10 times, the guide rod width. At these ratios, a particularly good trade-off between support strength and low aerodynamic impact can be achieved. The term guide rod length refers to the extension of the guide rod in the longitudinal direction of the aircraft, and the term guide rod width refers to the extension in a direction transverse to the aircraft.

[0018] According to another embodiment, the guide rod has a wing shape. In the case of a wing shape, the guide rod has a particularly low impact on the aerodynamics of the aircraft. The wing can be, for example, a wing recommended by the National Advisory Committee for Aeronautics (NACA).

[0019] According to another embodiment, the guide rod has a guide rod height and the height extension of the lighting system is between 60% and 120%, in particular between 80% and 100%, of the guide rod height. At said ratio between the guide rod height and the height extension of the lighting system, a particularly advantageous position of the lighting system above / below the aircraft fuselage can be achieved, thereby providing a highly unobstructed environment for light output while maintaining height stability across the aircraft beacon light. The height extension of the lighting system can be defined as the height of the envelope around the plurality of light sources, the light optics and the lens cover. The guide rod height as well as the height extension of the lighting system refers to the extension of the components in the vertical direction of the aircraft, i.e. in the z-direction of the aircraft.

[0020] According to another embodiment, the guide rod has a guide rod height between 20 mm and 80 mm, in particular between 30 mm and 50 mm. When mounting the aircraft beacon light to an aircraft fuselage, the guide rod height may be measured from the aircraft fuselage to the carrier of the support structure.

[0021] According to another embodiment, the plurality of light sources are spaced between 30 mm and 90 mm, in particular between 40 mm and 60 mm, from the aircraft fuselage. In other words, when the aircraft beacon light is mounted to the aircraft fuselage, the aircraft beacon light has a configuration such that the plurality of light sources are arranged between 30 mm and 90 mm, in particular between 40 mm and 60 mm, relative to the aircraft fuselage.

[0022] According to another embodiment, the support structure has a base for mounting to an aircraft fuselage, the base being spaced from the carrier by a guide rod. In particular, the base may have a cross-sectional base extension that is larger than the cross-sectional extension of the guide rod. In this way, the base provides additional stability to the aircraft beacon light at a location where the aerodynamic influence is smaller than at the guide rod. The base may be shaped in such a way that it can be mounted flush with the aircraft fuselage. In particular, the base may have a dish-like shape that can be inserted into a corresponding recess in the aircraft fuselage. The height extension discussed above may be measured relative to the upper surface of the base.

[0023] According to another embodiment, the carrier has a central portion and the plurality of light sources are arranged around the central portion. In this way, the plurality of light sources have an arrangement on the carrier that corresponds well to the 360° light output requirements of an aircraft beacon light. In particular, the plurality of light sources may be arranged along a circular contour.

[0024] According to another embodiment, the plurality of light sources face away from the carrier, and the lamp optics comprises a lens structure, the lens structure being arranged above the plurality of light sources and being configured to reflect laterally outwardly a first portion of light emitted by the plurality of light sources via total internal reflection. Directing the first portion of light of the plurality of light sources laterally outwardly via total internal reflection may allow for desirable redirection of the light in a spatially efficient manner. The first portion of light may enter the lens structure at a light entry surface, undergo total internal reflection at a first total internal reflection surface, and exit the lens structure at a light exit surface. The lens structure may be placed in close proximity to the plurality of light sources, and efficient redirection of light may be achieved without the need for a more substantial reflector structure. Furthermore, the use of a lens structure and its total internal reflection properties may allow for the elimination of metal reflectors provided in previous approaches, which may result in lower maintenance.

[0025] According to another embodiment, the lens structure is a monolithic structure. In other words, the lens structure may be a single lens body arranged above a plurality of light sources. Specifically, the lens structure may be a monolithic, substantially annular structure. In this way, the lens structure may be conveniently arranged above the plurality of light sources. In an alternative, the lens structure may include two or more individual lenses, each of which is arranged above one or more of the plurality of light sources.

[0026] According to another embodiment, the lens structure is made of silicone. Making the lens structure out of silicone allows providing a lens structure with low sensitivity to the harsh operating environment of an aircraft. In particular, silicone is suitable for withstanding aggressive chemicals that may be present in the aircraft environment during de-icing or due to exhaust from jet engines. Moreover, silicone allows providing the desired optical effect without corrosion problems. Furthermore, the lens structure can be conveniently molded from silicone.

[0027] According to another embodiment, the lens structure is overmolded over the plurality of light sources. In this way, a particularly dense and compact implementation of the aircraft beacon light can be achieved. Moreover, overmolding the lens structure over the plurality of light sources can allow for a small number of optical boundary surfaces, thereby contributing to the overall efficiency of the aircraft beacon light. Furthermore, overmolding the lens structure over the plurality of light sources allows for a mechanically strong attachment between the light sources and the lens structure.

[0028] According to another embodiment, the lens structure is configured to reflect a second portion of the light emitted by the plurality of light sources laterally inwardly via total internal reflection. In this way, a very large portion of the light emitted by the plurality of light sources can be redirected to a portion of the beacon light output where the highest light intensity is required. For example, redirecting the light laterally outwardly via total internal reflection may be primarily used to meet light intensity requirements in an angular range between 0° and 10° relative to the horizontal plane, while redirecting the light laterally inwardly via total internal reflection may be used to meet light intensity requirements in an angular range between 10° and 30° relative to the horizontal plane.

[0029] According to another embodiment, the plurality of light sources are arranged in a substantially rotationally symmetrical manner. The plurality of light sources may be arranged along a circular contour around a central portion of the carrier. Additionally or alternatively, the lamp optics, in particular the lens structure, may be of a substantially rotationally symmetrical design. The plurality of light sources and / or the arrangement of the lamp optics may be rotationally symmetrical with respect to an axis passing through the central portion of the carrier.

[0030] According to another embodiment, the lighting system has a horizontal reference plane, wherein the plurality of light sources are arranged on the horizontal reference plane, and the red flashing beacon light output extends to the guide rod side of the horizontal reference plane. In other words, in addition to providing the beacon light output on the distal side of the horizontal reference plane, the aircraft beacon light is configured to also provide some light output on the proximal side of the horizontal reference plane, i.e., on the guide rod side of the horizontal reference plane. In this way, the spacing of the lighting system of the aircraft beacon light from the aircraft fuselage can be used to extend the beacon light output to more than one of the two hemispheres. For example, in the case where the aircraft beacon light is arranged on the top of the aircraft fuselage, the beacon light output can extend slightly to the lower hemisphere, i.e., to below the aircraft in the optical far field. Conversely, in the case where the aircraft beacon light is arranged on the bottom of the aircraft fuselage, the beacon light output can extend slightly to the upper hemisphere, i.e., to above the aircraft in the optical far field. In this way, the beacon light output may be used to fill in gaps in the overall beacon light output around the aircraft that may be produced by engines, wingtips, or other exposed structure.

[0031] According to another embodiment, the red flashing beacon light output extends on the guide rod side of the horizontal reference plane to an angular range between 0° and 5°, more particularly between 0° and 10° relative to said horizontal reference plane.

[0032] According to another embodiment, the support structure includes at least one lightning arrester. In a specific embodiment, the support structure may include two lightning arresters, such as a front lightning arrester and a rear lightning arrester. The at least one lightning arrester may be arranged at the periphery of the lens cover of the lighting system. By providing one or more lightning arresters as part of the support structure, specifically at the periphery of the lens cover, the central lightning arrester provided through the lens cover adopted by previous methods can be eliminated. This in turn can eliminate the need for: a relatively cumbersome and often defective sealing of the central lightning arrester relative to the lens cover; and / or a relatively cumbersome handling of moisture entering the interior of the aircraft beacon light through the interface between the lens cover and the central lightning arrester.

[0033] According to another embodiment, the lens cover extends further away from the aircraft fuselage than the at least one lightning arrester. In other words, the lens cover extends further away from the guide rod of the support structure in the height dimension of the aircraft beacon light than the at least one lightning arrester. It has been surprisingly found that the lightning arrester provided as part of the support structure is effective in diverting lightning from the lens cover even when it does not extend as far from the aircraft fuselage as the lens cover.

[0034] According to another embodiment, the aircraft beacon light further comprises an electric dehumidifier, which is arranged between the carrier and the lens cover. In this way, moisture entering the interior space of the aircraft beacon light can be removed without relying on a venting structure based on a drain valve or a membrane. The electric dehumidifier can be arranged between the central portion of the carrier and the lens cover. In this way, the electric dehumidifier can provide particularly consistent removal of moisture within the interior of the aircraft beacon light.

[0035] Exemplary embodiments of the present invention also include an aircraft, the aircraft comprising at least one aircraft beacon light as described in any one of the above embodiments. The additional features, modifications and beneficial effects described above with respect to the exemplary embodiments of the aircraft beacon light are applicable to the aircraft in a similar manner.

[0036] According to another embodiment, the aircraft comprises an upper aircraft beacon light as described in any of the above embodiments mounted to the top portion of the fuselage of the aircraft, and a lower aircraft beacon light as described in any of the above embodiments mounted to the bottom portion of the fuselage of the aircraft or to the belly fairing of the aircraft. For each of the upper aircraft beacon light and the lower aircraft beacon light, the mounting can be done in a way that a guide rod spaces the carrier and the lighting system from the aircraft fuselage, i.e., the guide rod is arranged between the aircraft fuselage and the carrier of the aircraft beacon light. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Further exemplary embodiments of the present invention will be described below with reference to the accompanying drawings, in which:

[0038] Figure 1 A schematic top view of an aircraft according to an exemplary embodiment of the present invention is shown, which is equipped with two aircraft beacon lights according to an exemplary embodiment of the present invention;

[0039] Figure 2 The FAR requirements for aircraft beacon lights in an aircraft reference frame are illustrated, wherein a front view of an exemplary aircraft is shown;

[0040] Figure 3 A perspective view showing an aircraft beacon light according to an exemplary embodiment of the present invention;

[0041] Figure 4 Show Figure 3 A front view of an aircraft beacon light;

[0042] Figure 5 Show Figure 3 A horizontal cross-sectional view of an aircraft beacon light;

[0043] Fig. 6A Show Figure 3 The vertical cross-sectional view of the aircraft beacon light of FIG. Figure 6B showing enlarged views of selected parts thereof;

[0044] Figure 7 Show Figure 3 a perspective view of selected components of an aircraft beacon light; and

[0045] Figure 8 A front view of an aircraft according to an exemplary embodiment of the invention is shown which is equipped with two aircraft beacon lights according to an exemplary embodiment of the invention. DETAILED DESCRIPTION

[0046] Figure 1 An aircraft 100 is shown according to an exemplary embodiment of the present invention. Figure 1 The aircraft 100 is an airplane, in particular a large commercial passenger plane or a cargo plane. It should be noted that other types of aircraft, such as a helicopter, can also be implemented according to exemplary embodiments of the present invention.

[0047] Aircraft 100 has a fuselage 104. Two wings 106 are attached to the right and left sides of fuselage 104. Each of wings 106 carries a respective engine 108. In addition, two horizontal stabilizers 110 and a vertical stabilizer 112 are mounted to the tail portion of fuselage 104. Likewise, it is noted that exemplary embodiments of the present invention encompass aircraft according to other designs and configurations.

[0048] Aircraft 100 includes two aircraft beacon lights 2 mounted to fuselage 104. The upper aircraft beacon light 2 is mounted to the top portion of fuselage 104 and is used Figure 1 The lower aircraft beacon light 2 is mounted to the bottom portion of the fuselage 104 and is used Figure 1 The upper and lower aircraft beacon lights 2 are consistent with exemplary embodiments of the present invention and will be referred to below. Figures 3 to 7 The details are described in detail. In operation, the aircraft beacon light 2 emits a flash of red light to provide the beacon light characteristics expected by other aircraft, ground personnel and space control. Specifically, the aircraft beacon light 2 can emit a flash of aviation red light.

[0049] Figure 2 The light intensity distribution of an upper aircraft beacon light and a lower aircraft beacon light required by Federal Aviation Regulations (FAR) when the upper aircraft beacon light and the lower aircraft beacon light are mounted to the top / bottom of an exemplary aircraft 100 are illustrated. Specifically, the light intensity distribution depicted reflects the requirements of FAR Section 25.1401. The light intensity distribution is shown as an angular distribution relative to a horizontal plane 200. Specifically, the light intensity distribution is shown in a vertical cross-sectional plane orthogonal to the longitudinal extension of the aircraft fuselage. However, because the FAR requirements are described as a rotationally symmetric distribution, that is, a distribution that is the same in all viewing directions from the aircraft beacon light, the light intensity distribution shown will appear the same in all vertical cross-sections passing through the center of the upper aircraft beacon light and through the center of the lower aircraft beacon light, respectively.

[0050] Figure 2 The depicted light intensity distribution of is as follows. A light intensity of 400 cd is required within an angular range between 0° and 5° relative to the horizontal plane 200. A light intensity of 240 cd is required within an angular range between 5° and 10° relative to the horizontal plane 200. A light intensity of 80 cd is required within an angular range between 10° and 20° relative to the horizontal plane 200. A light intensity of 40 cd is required within an angular range between 20° and 30° relative to the horizontal plane 200. A light intensity of 20 cd is required within an angular range between 30° and 75° relative to the horizontal plane 200. Therefore, in Figure 2 The required light intensity values ​​shown in the angular segments in represent the minimum light intensity values ​​specified by the FAR. Because the horizontal plane 200 is the plane with the highest required light intensity, it may also be referred to as the primary light output plane. The expression that the beacon light output achieves the FAR requirement or meets the FAR requirement or is consistent with the FAR requirement will be understood as the beacon light output meeting or exceeding the required minimum light intensity value.

[0051] Figures 3 to 7An exemplary aircraft beacon light satisfies Figure 2 The requirements described in .

[0052] Figure 3 A perspective view of an aircraft beacon light 2 according to an exemplary embodiment of the invention is shown. The aircraft beacon light 2 comprises a support structure 4 and a lighting system 6.

[0053] The support structure 4 includes a base 48, guide rods 42 and a carrier, which is blocked from moving in the Figure 3 The lighting system 6 includes a plurality of light sources, a light optical device and a lens cover 68. Figure 3 In the perspective view of FIG. 6 , only the lens cover 68 is depicted, wherein a plurality of light sources and light optics are arranged below the lens cover 68 .

[0054] The aircraft beacon light 2 also includes a fastener 8. The fastener 8 secures the lens cover 68 in place relative to the support structure 4, as will be explained in more detail with respect to FIG6. The fastener 8 has a bolt hole 80 through which a bolt can be inserted in order to secure the fastener, and thus the lens cover 68, to the carrier of the support structure 4.

[0055] The support structure 4 supports the lighting system 6 and is configured to be mounted to the aircraft fuselage. The carrier of the support structure 4 is a disc-shaped structure that supports the lens cover 68 and other components of the lighting system 6. The base 48 is also a disc-shaped structure. The base 48 can be mounted to the aircraft fuselage. The guide rod 42 spaced the base 48 from the carrier. In this way, when the aircraft beacon light 2 is mounted on the aircraft fuselage, the guide rod 42 spaced the lighting system 6 from the aircraft fuselage.

[0056] The guide rod 42 has a front end 44 and a rear end 46. The guide rod 42 is an elongated structure whose length is significantly greater than its width. When mounted to an aircraft fuselage, the longitudinal extension of the guide rod 42 from its front end 44 to its rear end 46 is aligned with the longitudinal extension of the aircraft. Figure 3 The guide rod 42 has a wing shape between its front end 44 and its rear end 46, as will be described below with reference to FIG. Figure 5 described.

[0057] The support structure 4 also includes two lightning arresters 52, namely a front lightning arrester and a rear lightning arrester. The lightning arresters 52 extend through the fastener 8. They are arranged in close proximity to the periphery of the lens cover 68.

[0058] The fastener 8 surrounds the proximal portion of the lens cover 68 of the lighting system 6. This enables the lens cover 68 to be clamped to the support structure 4 around the periphery of the lens cover 68. The fastener 8 is also shaped for aerodynamic efficiency.

[0059] Figure 4 Show Figure 3 4. As described above, the support structure 4 of the aircraft beacon light 2 includes a base 48, a guide rod 42 and a carrier 40. Figure 4 It can be seen in Figure 3 The lower side of the carrier 40 is blocked from being viewed in the viewing direction. Figure 4 In the front view of FIG. 4 , the carrier 40 extends to the left and right of the guide rod 42. The guide rod 42 has a much smaller transverse cross-section than the carrier 40. It also has a much smaller transverse cross-section than the base 48. The fastener 8 has a slightly larger transverse extension than the carrier 40 and the lens cover 68. The fastener 8 surrounds the carrier 40 and the proximal portion of the lens cover 68, thereby fixing the lens cover 68 to the carrier 40.

[0060] Figure 5 Show Figure 3 A horizontal cross-sectional view of an aircraft beacon light 2. Figure 5 The cross-sectional plane passes through the guide rod 42. The viewing direction is toward the base 48 of the support structure 4.

[0061] In the exemplary embodiment depicted, the base 48 includes four mounting holes 50. To mount the aircraft beacon light 2 to the aircraft fuselage, four bolts are inserted through the mounting holes 50, thereby securing the base 48 to the aircraft fuselage. The aircraft fuselage may have a recessed portion that corresponds in shape and size to the disc-shaped base 48. In this way, when the aircraft beacon light 2 is mounted to the aircraft fuselage, the upper surface of the base 48 may be flush with the outer surface of the aircraft fuselage.

[0062] In the exemplary embodiment depicted, the guide rod 42 has an airfoil shape. The airfoil shape widens to its maximum width fairly closely with a front end 44, and tapers over most of its longitudinal extension to a rear end 46. In the exemplary embodiment depicted, the airfoil shape is consistent with the NACA 0012 airfoil specification. It is noted that other airfoil shapes are possible.

[0063] In the exemplary embodiment depicted, the guide rod 42 is hollow. The wall structure forming the wing is thin compared to the outer extension of the guide rod 42. It is pointed out that the guide rod 42 can also be a solid structure.

[0064] FIG6 shows Figure 3 6 is a vertical cross-sectional view of an aircraft beacon light 2. The cross-sectional plane of FIG. 6 is a longitudinal cross-sectional plane in the aircraft reference system and passes through the center of the aircraft beacon light 2. Fig. 6A The entirety of the aircraft beacon light 2 is shown, and Figure 6B Shows enlarged views of selected components thereof.

[0065] As previously described, the aircraft beacon light 2 includes a support structure 4 and a lighting system 6. As further described previously, the support structure 4 includes a base 48, a guide rod 42, and a carrier 40. The guide rod 42 spaces the base 48 from the carrier 40. Where the guide rod 42 is a hollow structure in the exemplary embodiment depicted, the carrier 40 closes the hollow structure on the distal side. In the exemplary embodiment depicted, the carrier 40 supports the lighting system 6, as will be explained in more detail below.

[0066] The support structure 4 further comprises two lightning arresters 52, which are arranged on the front and rear parts of the carrier 40. In the exemplary embodiment of Fig. 6, the base 48, the guide rods 42, the carrier 40 and the lightning arresters 52 are integrally formed.

[0067] The lighting system 6 includes a plurality of light sources 60, a lamp optic 62, a lens cover 68, a circuit board 70 (e.g., a printed circuit board), and an electric dehumidifier 72. The circuit board is mounted to the carrier 40, for example, via attachment screws or other suitable attachment members. The plurality of light sources 60, the lamp optic 62, and the electric dehumidifier 72 are mounted to the circuit board 70 and are thus supported by the carrier 40. The circuit board 70 may carry other components, such as a control unit, and may provide electrical connections between the components, such as electrical connections between an onboard power grid, a control unit, and a plurality of light sources.

[0068] The lens cover 68 is a dome-shaped structure. The proximal portion of the lens cover 68 is placed around the step in the upper surface of the carrier 40. In this way, the lens cover 68 is prevented from moving sideways by the carrier 40. In the exemplary embodiment depicted, the proximal portion of the lens cover 68 is arranged between the step in the upper surface of the carrier 40 and the arrester 52. In this way, the arrester 52 is arranged in close proximity to the periphery of the lens cover 68.

[0069] The aircraft beacon light 2 further comprises an O-ring 10 arranged between the lens cover 68 and the carrier 40 of the support structure 4. By means of the O-ring 10, an effective sealing of the interior space of the aircraft beacon light 2 between the carrier 40 and the lens cover 68 is achieved. The lens cover 68 is clamped to the support structure 4, in particular, to the carrier 40, by means of the fastener 8.

[0070] A plurality of light sources 60, a lamp optical device 62 and an electric dehumidifier 72 are arranged between the carrier 40 and the lens cover 68, i.e., in the interior space of the aircraft beacon light. The plurality of light sources 60 are arranged in a circular manner around the central portion 41 of the carrier 40. In the exemplary embodiment depicted, the plurality of light sources 60 are red LEDs. The plurality of light sources 60 face away from the carrier 40.

[0071] In the exemplary embodiment depicted, the light optics 62 include an annular lens structure that is disposed over, and in particular, overmolded over, the plurality of light sources 60. The annular lens structure may be made of silicone or other suitable transparent or translucent material (eg, PMMA).

[0072] The annular lens structure has a first total internal reflection surface 64 and a second total internal reflection surface 66. The first total internal reflection surface 64 reflects a first portion of the light emitted by the plurality of light sources 60 laterally outward. The second total internal reflection surface 66 reflects a second portion of the light emitted by the plurality of light sources 60 laterally inward. The redirection of light by the annular lens structure is illustrated via the exemplary light rays in FIG. 6 . The redirection of light from the plurality of LEDs 60 via the first total internal reflection surface 64 and the second total internal reflection surface 66 allows the FAR requirements of the aircraft beacon light to be effectively met while also allowing a low height of the light optic 62. The plurality of light sources 60, the light optic 62, and the lens cover 68 are arranged in a rotationally symmetrical manner around the axis of rotation 74.

[0073] An electric dehumidifier 72 is arranged in the center of the annular lens structure. An electric dehumidifier is a device that converts water into hydrogen and oxygen with the help of electrical energy. The hydrogen produced is highly elusive and can escape the seal. In this way, water and moisture accumulated in the interior space of the aircraft beacon light can be effectively removed.

[0074] Spacing the lighting system 6 from the aircraft fuselage via the guide rods 42, redirecting the light via total internal reflection, the arrangement of the lightning arrester 52 at the periphery of the lens cover 68, and the provision of the electric dehumidifier 72 cooperate to provide an overall advantageous system design. Spacing the lighting system 6 from the aircraft fuselage via the guide rods 42 and redirecting the light via total internal reflection allow for efficient implementation of the functionality of an aircraft beacon light with a low height extension of the lighting system 6. With the low height extension of the lighting system 6, the lightning arrester 52 is sufficient to divert potential lightning strikes from the lens cover 68, despite the lightning arrester being placed around the periphery of the lens cover 68 and having a smaller height extension than the lens cover 68. Providing the lightning arrester 52 outside the lens cover 68 eliminates the need for a central lightning arrester extending through the lens cover 68. In the absence of such a central lightning arrester, sealing of the interior space of the aircraft beacon light 2 can be performed in a particularly effective manner. This results in a small amount of moisture / water being trapped within the interior space of the aircraft beacon light 2 , and this small amount of water / moisture can be conveniently handled by an electrical dehumidifier 72 .

[0075] In the exemplary embodiment depicted, the opening angle of the light output is about 180°. In this way, the aircraft beacon light 2 can meet FAR requirements in the upper hemisphere or the lower hemisphere in the aircraft reference frame. It is noted that the opening angle of the beacon light output can also be more than 180° in one or more or all vertical cross-sections through the aircraft beacon light 2. This can be achieved by a modified geometry of the first total internal reflection surface 64 or by other suitable means for directing the light accordingly. Figure 8 The effect of an opening angle greater than 180° of the beacon light output is described and explained in more detail.

[0076] In operation, the aircraft beacon light 2 emits a red flashing beacon light output. Specifically, the plurality of light sources may be controlled to illuminate in a pulsed manner. More specifically, the plurality of light sources may be controlled to illuminate in a pulsed mode, which produces a human observer's perception of a series of flashes of red light. The aircraft beacon light 2 may include a control unit that causes the plurality of light sources to emit a series of flashes. The control unit may be coupled to an onboard power supply and may provide current pulses to the plurality of LEDs.

[0077] Figure 7 A three-dimensional perspective view of a circuit board 70, a plurality of light sources 60, a lamp optic 62, and an electric dehumidifier 72 is shown. Figure 7 The annular structure of the lamp optic 62 is shown, including its first total internal reflection surface 64 and its second total internal reflection surface 66, and the arrangement of a plurality of light sources 60 along a circular outline.

[0078] Figure 8 An aircraft 100 according to an exemplary embodiment of the present invention is shown, which is equipped with two aircraft beacon lights 2 according to an exemplary embodiment of the present invention. In particular, the aircraft 100 has an upper beacon light 2 according to an exemplary embodiment of the present invention mounted to the top portion of the aircraft fuselage 104. In addition, the aircraft 100 has a lower aircraft beacon light 2 mounted to the bottom portion of the aircraft fuselage 104. For ease of illustration, only the guide rod and the lens cover of the aircraft beacon light 2 are depicted. Moreover, the guide rod and the lens cover are depicted highly schematically and are larger than if they were depicted to scale. In this way, the spacing of the lens cover and thus the lighting system from the aircraft fuselage 104 is more clearly illustrated.

[0079] Both the upper aircraft beacon light 2 and the lower aircraft beacon light 2 provide beacon light outputs having an opening angle of more than 180°, which is caused by Figure 8. In other words, both of the depicted aircraft beacon lights 2 provide beacon light output that extends to the guide rod side of the horizontal reference plane passing through the plurality of light sources, i.e., to the side of the aircraft fuselage 104 that passes through the horizontal reference plane of the plurality of light sources. In this way, the upper and lower aircraft beacon lights 2 can help alleviate the shading of the beacon light output that may be caused by the engine 108, the wing tip 116, or other aircraft structure. Specifically, in the far field, the beacon light output of the upper aircraft beacon light 2 can fill in the gap in the beacon light output caused by the engine 108 relative to the light emitted by the lower aircraft beacon light 2. Similarly, in the far field, the beacon light output of the lower aircraft beacon light 2 can fill in the gap in the beacon light output caused by the wing tip 116 relative to the light emitted by the upper aircraft beacon light 2. Therefore, exemplary embodiments of the present invention can allow for a more complete beacon light output around the aircraft. The opening angle α may be, for example, between 185° and 210°, in particular between 190° and 200°. An opening angle α of 190° means that the beacon light output extends to an angular range between 0° and 5° on the guide rod side of a horizontal reference plane passing through the aircraft beacon light 2, and an opening angle α of 200° means that the beacon light output extends to an angular range between 0° and 10° on the guide rod side of a horizontal reference plane passing through the aircraft beacon light 2.

[0080] Although the present invention has been described with reference to exemplary embodiments, it will be appreciated by those skilled in the art that various changes may be made and equivalents may be used to replace its elements without departing from the scope of the present invention. In addition, many modifications may be made to adapt specific circumstances or materials to the teachings of the present invention without departing from the essential scope of the present invention. Therefore, it is expected that the present invention is not limited to the specific embodiments disclosed, but rather, the present invention will include all embodiments that fall within the scope of the appended claims.

Claims

1. An aircraft beacon light (2) for mounting on an aircraft fuselage (104), comprising: A supporting structure (4), the supporting structure comprising: a carrier (40), and a guide rod (42) for supporting the carrier (40) and for spacing the carrier (40) from the aircraft fuselage (104); as well as A lighting system (6), the lighting system being supported by the supporting structure (4), the lighting system (6) comprising: a plurality of light sources (60), a light optic (62) for redirecting at least a portion of the light emitted by the plurality of light sources (60), and a lens cover (68), wherein the plurality of light sources (60) and the light optics (62) are arranged between the carrier (40) and the lens cover (68); wherein the aircraft beacon light (2) is configured to emit a red flashing beacon light output during operation; wherein the guide rod (42) has an elongated shape between a front end (44) and a rear end (46) aligned with the longitudinal extension of the aircraft; and Wherein, the lens cover (68) does not surround the guide rod (42).

2. An aircraft beacon light (2) according to claim 1, wherein the carrier (40) has a cross-sectional carrier extension, and the guide rod (42) has a cross-sectional guide rod extension, and wherein the size of the cross-sectional carrier extension is between 5 times and 40 times, specifically between 10 times and 30 times, and more specifically between 15 times and 25 times, the size of the cross-sectional guide rod extension.

3. An aircraft beacon light (2) according to claim 1 or 2, wherein the guide rod (42) has a guide rod length and a guide rod width, and wherein the guide rod length is between 3 times and 15 times the guide rod width, specifically between 5 times and 12 times, and more specifically between 8 times and 10 times.

4. The aircraft beacon light (2) according to claim 1 or 2, wherein the guide rod (42) has a wing shape.

5. An aircraft beacon light (2) according to claim 1 or 2, wherein the guide rod (42) has a guide rod height, and wherein the height extension of the lighting system (6) is between 60% and 120%, in particular between 80% and 100%, of the guide rod height.

6. The aircraft beacon light (2) according to claim 1 or 2, wherein the plurality of light sources (60) are spaced between 30 mm and 90 mm, in particular between 40 mm and 60 mm, from the aircraft fuselage (104).

7. An aircraft beacon light (2) according to claim 1 or 2, wherein the support structure (4) has a base (48) for mounting to the aircraft fuselage (104), the base (48) being spaced apart from the carrier (40) by the guide rod (42).

8. An aircraft beacon light (2) according to claim 1 or 2, wherein the carrier (40) has a central portion (41), and wherein the plurality of light sources (60) are arranged around the central portion (41).

9. An aircraft beacon light (2) according to claim 1 or 2, wherein the plurality of light sources (60) are facing away from the carrier, and wherein the light optics (62) include a lens structure, which is arranged above the plurality of light sources (60) and is configured to reflect a first portion of the light emitted by the plurality of light sources (60) laterally outward via total internal reflection.

10. An aircraft beacon light (2) according to claim 1 or 2, wherein the lighting system (6) has a horizontal reference plane, wherein the plurality of light sources (60) are arranged on the horizontal reference plane, and wherein the red flashing beacon light output extends to the guide rod side of the horizontal reference plane, specifically to an angular range between 0° and 5° relative to the horizontal reference plane, more specifically to an angular range between 0° and 10° relative to the horizontal reference plane.

11. Aircraft beacon light (2) according to claim 1 or 2, wherein the support structure (4) comprises at least one lightning arrester (52), which is arranged in particular at the periphery of the lens cover (68).

12. The aircraft beacon light (2) of claim 11, wherein the lens cover (68) extends further away from the aircraft fuselage (104) than the at least one lightning arrester (52).

13. The aircraft beacon light (2) according to claim 1 or 2, further comprising an electric dehumidifier (72), wherein the electric dehumidifier (72) is arranged between the carrier (40) and the lens cover (68), specifically between the central portion (41) of the carrier (40) and the lens cover (68).

14. An aircraft (100), comprising at least one aircraft beacon light (2) according to any one of the preceding claims, the at least one aircraft beacon light specifically comprising an upper aircraft beacon light mounted to the top portion of the fuselage of the aircraft, and a lower aircraft beacon light mounted to the bottom portion of the fuselage of the aircraft or to the belly fairing of the aircraft.

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