Integrated wingtip lighting system and aircraft

Abstract

The invention relates to an integrated wingtip lighting system and an aircraft. The integrated wingtip lighting system comprises a shell, a navigation lamp light source printed board, a navigation lamp reflecting component, an anti-collision lamp light source printed board and an anti-collision lamp lens. Wherein the navigation lamp light source printed board is installed on a first installation plane of the shell, the anti-collision lamp light source printed board is installed on a second installation plane of the shell, the first installation plane and the second installation plane are adjacent to each other, the navigation lamp reflecting component is installed on one side of the navigation lamp light source printed board, and the first installation plane is consistent with the course of an airplane. A second installation angle ranging from 28 degrees to 32 degrees is formed between the second installation plane and the course of the airplane, an extension angle ranging from 26 degrees to 30 degrees is formed between the extension plane of the navigation lamp reflecting component and the course of the airplane, and the anti-collision lamp lens is installed above the anti-collision lamp light source printed board.

Description

Technical Field

[0001] The present invention relates to an integrated wing tip lighting system and an aircraft including the integrated wing tip lighting system. Background Art

[0002] External lighting of civil aircraft provides sufficient lighting for various operating stages of the aircraft at night. Red / green navigation lights are used to provide the heading information of the aircraft for other aircraft and ground personnel during flight. Anti-collision lights make the aircraft easier to identify in the air and on the ground.

[0003] Civil aircraft have strict requirements on the optical performance and safety of external lighting. A too large wing tip lamp cover is not conducive to reducing the probability of failure and the convenience of installing the lamp cover. Red / green navigation lights and wing tip white anti-collision lights are installed at the left and right wing tips of the aircraft. Nowadays, most wing tip white anti-collision lights and red / green navigation lights adopt a separate lamp body / case design and are respectively installed in the wing tip lamp cover, which requires a large installation space and a high frequency of removing the wing tip lamp cover. Summary of the Invention

[0004] An object of the present invention is to provide an integrated wing tip lighting system, which can overcome at least some defects of the prior art, can reduce the size and weight of the wing tip lighting system, reduce the size of the wing tip lamp cover, and the installation positions of the navigation lights and the anti-collision lights are such that their respective light-emitting surfaces do not interfere with each other.

[0005] The above object of the present invention is achieved by an integrated wing tip lighting system, which includes a housing, a navigation light source printed circuit board, a navigation light reflector, an anti-collision light source printed circuit board, and an anti-collision light lens;

[0006] Wherein, the navigation light source printed circuit board is installed on the first installation plane of the housing, the anti-collision light source printed circuit board is installed on the second installation plane of the housing, the first installation plane and the second installation plane are adjacent to each other, the navigation light reflector is installed on one side of the navigation light source printed circuit board, the first installation plane is consistent with the aircraft heading, the second installation plane forms a second installation angle of 28 - 32 degrees with the aircraft heading, the extension plane of the navigation light reflector forms an extension angle of 26 - 30 degrees with the aircraft heading, and the anti-collision light lens is installed above the anti-collision light source printed circuit board.

[0007] According to the above technical solution, the integrated wing tip lighting system of the present invention can achieve the following beneficial technical effects: it can reduce the size and weight of the wing tip lighting system, reduce the size of the wing tip lamp cover, and the installation positions of the navigation lights and the anti-collision lights are such that their respective light-emitting surfaces do not interfere with each other.

[0008] Preferably, the second mounting angle formed by the second mounting plane where the anti-collision light source printed circuit board is located and the aircraft heading is 30 degrees.

[0009] According to the above technical solution, the integrated wing tip lighting system of the present invention can achieve the following beneficial technical effects: through the preferred second mounting angle, it can better ensure that the horizontal light output angle of the anti-collision light is -10 to 100 degrees.

[0010] Preferably, the extension angle formed by the extension plane of the navigation light reflecting member and the aircraft heading is 28 degrees.

[0011] According to the above technical solution, the integrated wing tip lighting system of the present invention can achieve the following beneficial technical effects: through the preferred extension angle, it can better ensure that the horizontal light output angle of the navigation light is 0 to 110 degrees.

[0012] Preferably, the navigation light reflecting member is in the shape of a reflecting bowl.

[0013] According to the above technical solution, the integrated wing tip lighting system of the present invention can achieve the following beneficial technical effects: through the preferred shape and structure of the navigation light reflecting member, it can ensure that the LED light deviates back to the dihedral angle area from other angles, and make the light distribution more uniform, solving the problem that the light intensity at the edge of the light emitting surface is not strong enough.

[0014] Preferably, the navigation light reflecting member covers the middle part of the navigation light source printed circuit board, and there are gaps on both sides of the navigation light reflecting member without covering the remaining part of the navigation light source printed circuit board.

[0015] According to the above technical solution, the integrated wing tip lighting system of the present invention can achieve the following beneficial technical effects: since the navigation light reflecting member only covers the middle part of the navigation light source printed circuit board, the light intensity within the navigation light reflecting member is strengthened, and the light on both sides of the navigation light reflecting member can cross the navigation light reflecting member, so as to better ensure that the horizontal light output angle of the navigation light is 0 to 110 degrees.

[0016] Preferably, the ratio of the length of the covered part of the navigation light reflecting member to the length of the un-covered part on one side is 2.8 to 3.2:1.

[0017] According to the above technical solution, the integrated wing tip lighting system of the present invention can achieve the following beneficial technical effects: through the preferred ratio of the length of the covered part of the navigation light reflecting member to the length of the un-covered part on one side, it can better ensure that the horizontal light output angle of the navigation light is 0 to 110 degrees.

[0018] Preferably, the two sides of the covering part of the navigation light reflector part are not perpendicular to the bottom side of the covering part of the navigation light reflector part, but form an angle of 1 to 3 degrees with respect to the vertical line of the bottom side.

[0019] According to the above technical solution, the integrated wing tip lighting system of the present invention can achieve the following beneficial technical effects: Since the two sides of the covering part of the navigation light reflector part form an angle of 1 to 3 degrees with respect to the vertical line of the bottom side, the top side of the covering part of the navigation light reflector part is slightly shortened with respect to the bottom side, and the light distribution is more uniform, which can better ensure that the horizontal light output angle of the navigation light is 0 to 110 degrees.

[0020] Preferably, the integrated wing tip lighting system further includes a lens retaining ring for pressing the anti-collision light lens above the anti-collision light source printed circuit board and mounting the anti-collision light lens on the housing.

[0021] According to the above technical solution, the integrated wing tip lighting system of the present invention can achieve the following beneficial technical effects: Through the appropriately arranged lens retaining ring, the anti-collision light lens can be better mounted above the anti-collision light source printed circuit board and on the housing.

[0022] Preferably, the navigation light source printed circuit board adopts a dual-module design.

[0023] According to the above technical solution, the integrated wing tip lighting system of the present invention can achieve the following beneficial technical effects: Each module is powered by a different constant current drive module, and the redundant design can ensure the normal navigation of the aircraft even if a problem occurs in a single module of the red / green navigation light.

[0024] The above object of the present invention is also achieved by an aircraft, which includes the integrated wing tip lighting system as described in any of the above aspects.

[0025] According to the above technical solution, the aircraft of the present invention can achieve the following beneficial technical effects: It can reduce the size and weight of the wing tip lighting system, reduce the size of the wing tip lamp cover, and the installation positions of the navigation light and the anti-collision light make their respective light-emitting surfaces non-interfering. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 is a perspective view of the integrated wing tip lighting system according to an embodiment of the present invention.

[0027] Figure 2 is a side view of the integrated wing tip lighting system according to an embodiment of the present invention.

[0028] Figure 3 is the light intensity distribution diagram of the red / green navigation light.

[0029] Figure 4Schematic diagram of the navigation light reflector component of the integrated wing tip lighting system according to an embodiment of the present invention.

[0030] Figure 5 Schematic diagram of the light output angle of the integrated wing tip lighting system according to an embodiment of the present invention.

[0031] List of reference numerals

[0032] 1: Housing;

[0033] 2: Navigation light source printed circuit board;

[0034] 3: Navigation light reflector component;

[0035] 4: Anti-collision light source printed circuit board;

[0036] 5: Anti-collision light lens;

[0037] 6: Lens retaining ring;

[0038] 11: First mounting plane;

[0039] 12: Second mounting plane;

[0040] A2: Second mounting angle;

[0041] A3: Extension angle;

[0042] C: Course. Detailed implementation manners

[0043] The following will describe the detailed implementation manners of the present invention. It should be noted that in the process of the specific description of these implementation manners, for the sake of concise description, this specification cannot describe all the features of the actual implementation manners in detail. It should be understood that in the actual implementation process of any implementation manner, just as in the process of any engineering project or design project, in order to achieve the specific goals of the developer and to meet the system-related or business-related limitations, various specific decisions are often made, and these will also change from one implementation manner to another. In addition, it should also be understood that although the efforts made in this development process may be complex and lengthy, for those of ordinary skill in the art related to the content disclosed in the present invention, some design, manufacturing or production changes based on the technical content disclosed in this disclosure are only conventional technical means and should not be understood as the content of this disclosure being insufficient.

[0044] Unless otherwise defined, technical terms or scientific terms used in the claims and the specification shall have the ordinary meanings understood by those of ordinary skill in the technical field to which the present invention pertains. The terms "first", "second" and similar terms used in the specification and claims of this patent application for the invention do not denote any order, quantity or importance, but are merely used to distinguish different components. The terms such as "a" or "an" do not denote a limitation of quantity, but rather denote the existence of at least one. The terms such as "comprising" or "including" mean that the elements or objects appearing before "comprising" or "including" cover the elements or objects listed after "comprising" or "including" and their equivalent elements, and do not exclude other elements or objects. The terms such as "connected" or "coupled" are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0045] In the following description, in order to clearly show the structure and working mode of the present invention, many directional terms will be used for description. However, the terms such as "front", "rear", "left", "right", "outer", "inner", "outward", "inward", "up", "down", etc. should be understood as convenient terms, rather than restrictive terms.

[0046] Figure 1 is a perspective view of an integrated wingtip lighting system according to an embodiment of the present invention. Figure 2 is a side view of an integrated wingtip lighting system according to an embodiment of the present invention. Figure 3 is a light intensity distribution diagram of a red / green navigation light.

[0047] Figure 4 is a schematic diagram of a navigation light reflecting component of an integrated wingtip lighting system according to an embodiment of the present invention.

[0048] Figure 5 is a schematic diagram of the light output angle of an integrated wingtip lighting system according to an embodiment of the present invention.

[0049] As Figures 1 to 5 shown, an integrated wingtip lighting system according to an embodiment of the present invention includes a housing 1, a navigation light source printed circuit board 2, a navigation light reflecting component 3, an anti-collision light source printed circuit board 4, and an anti-collision light lens 5.

[0050] The navigation light source printed circuit board 2 is mounted (e.g., by screws) on a first mounting plane 11 of the housing 1, and the navigation light source printed circuit board 2 provides outgoing light for the navigation light. The anti-collision light source printed circuit board 4 is mounted (e.g., by screws) on a second mounting plane 12 of the housing 1, and the anti-collision light source printed circuit board 4 provides outgoing light for the anti-collision light. The first mounting plane 11 and the second mounting plane 12 are adjacent to each other. The navigation light reflecting component 3 is mounted (e.g., by screws) on one side of the navigation light source printed circuit board 2.

[0051] The first mounting plane 11 is aligned with the aircraft heading C. That is to say, the first mounting plane 11 forms a first mounting angle A1 of 0 degrees with the aircraft heading C. The second mounting plane 12 forms a second mounting angle A2 of 28 to 32 degrees with the aircraft heading C. The extension plane of the navigation light reflecting member 3 forms an extension angle A3 of 26 to 30 degrees with the aircraft heading C.

[0052] The anti-collision light lens 5 is installed above the anti-collision light source printed circuit board 4, so that the light emitted from the anti-collision light source printed circuit board 4 can be emitted through the anti-collision light lens 5.

[0053] According to the above technical solution, the integrated wing tip lighting system of the present invention can achieve the following beneficial technical effects: it can reduce the size and weight of the wing tip lighting system, reduce the size of the wing tip lamp cover, and the installation positions of the navigation lights and the anti-collision lights make their respective light-emitting surfaces non-interfering.

[0054] Specifically, the present invention integrates the navigation lights (red / green navigation lights) and the anti-collision lights into an integrated wing tip lighting system. Both are installed on the same housing 1 and are located within the same wing tip lamp cover. The first mounting plane 11 where the navigation light source printed circuit board 2 is located and the second mounting plane 12 where the anti-collision light source printed circuit board 4 is located are adjacent to each other, and their installation positions are quite compact. Therefore, it can reduce the size and weight of the wing tip lighting system and reduce the size of the wing tip lamp cover (the size of the wing tip lamp cover is reduced by at least 1 / 3 compared with the prior art), thereby reducing the possibility of the lamp cover cracking. Since the first mounting plane 11 is aligned with the aircraft heading C, the second mounting plane 12 forms a second mounting angle A2 of 28 to 32 degrees with the aircraft heading C, and the extension plane of the navigation light reflecting member 3 forms an extension angle A3 of 26 to 30 degrees with the aircraft heading C, the light-emitting surfaces of the navigation lights and the anti-collision lights do not interfere with each other, and it is ensured that the horizontal light-emitting angle of the navigation lights is 0 to 110 degrees, and the horizontal light-emitting angle of the anti-collision lights is -10 to 100 degrees. Due to the respective mounting angles of the navigation lights and the anti-collision lights, the light intensity of the red / green navigation lights within the horizontal 0° to 110° and vertical -90° to 90° dihedral angle and the light intensity of the wing tip white anti-collision lights within the horizontal -10° to 100° and vertical -90° to 90° are guaranteed.

[0055] In some embodiments, such as Figures 1 to 2As shown in the figure, the light source printed circuit board of the present invention (navigation light source printed circuit board 2 and / or anti-collision light source printed circuit board 4) preferably adopts an aluminum substrate with a higher thermal conductivity, which can conduct the heat generated on the LED to the housing 1 faster and better, thereby achieving heat dissipation. The power devices are mainly installed on the control printed circuit board. The control printed circuit board adopts an aluminum substrate and is treated with shell attachment, which can play a good role in heat dissipation. The heat dissipation path between the light source component and the housing 1 is shortened to reduce the thermal resistance. There is a control circuit unit in the housing 1 to control the operation of each light source printed circuit board. The housing material preferably uses 2024 aluminum alloy, which can play a good role in heat dissipation and weight reduction.

[0056] According to the optical requirements, the dihedral angle area of the navigation light is 0° to 110° horizontally and -90° to 90° vertically. The front-incorporated light A area is 10° to 20° horizontally and -90° to 90° vertically. The front-incorporated light B area is 20° to 90° horizontally and -90° to 90° vertically. The rear-incorporated light A area is 10° to 20° horizontally and -90° to 90° vertically. The rear-incorporated light B area is 20° to 90° horizontally and -90° to 90° vertically. The optical area is as Figure 3 shown.

[0057] In some embodiments, as Figure 2 shown, the second installation angle A2 formed by the second installation plane 12 where the anti-collision light source printed circuit board 4 is located and the aircraft heading C is 30 degrees. According to the above technical solution, the integrated wingtip lighting system of the present invention can achieve the following beneficial technical effects: through the better second installation angle, it can better ensure that the horizontal light output angle of the anti-collision light is -10 to 100 degrees.

[0058] In some embodiments, as Figure 2 shown, the extension angle A3 formed by the extension plane of the navigation light reflector 3 and the aircraft heading C is 28 degrees. According to the above technical solution, the integrated wingtip lighting system of the present invention can achieve the following beneficial technical effects: through the better extension angle, it can better ensure that the horizontal light output angle of the navigation light is 0 to 110 degrees.

[0059] In some embodiments, as Figures 1 to 2 shown, the navigation light reflector 3 is in the shape of a reflecting bowl. According to the above technical solution, the integrated wingtip lighting system of the present invention can achieve the following beneficial technical effects: through the better shape and structure of the navigation light reflector, it can ensure that the LED light deviates back to the dihedral angle area from other angles and make the light distribution more uniform, solving the problem of insufficient light intensity at the edge of the light-emitting surface.

[0060] If designed only according to the natural light-emitting angle of the LED beam, the beam will be scattered, resulting in insufficient light intensity in the left or right direction of the vertical axis. In this case, to meet the requirements of the light intensity distribution, a reflector bowl is installed near the LED to ensure that a part of the LED light is deviated from other angles and reflected back to the dihedral angle, so that the edge light intensity meets the requirements.

[0061] In some embodiments, as Figure 4 shown, the navigation light reflecting member 3 covers the middle part of the navigation light source printed circuit board 2, and there are gaps on both sides of the navigation light reflecting member 3 without covering the remaining part of the navigation light source printed circuit board 2. According to the above technical solution, the integrated wing tip lighting system of the present invention can achieve the following beneficial technical effects: Since the navigation light reflecting member 3 only covers the middle part of the navigation light source printed circuit board 2, the light intensity within the navigation light reflecting member 3 is enhanced, and the light on both sides of the navigation light reflecting member 3 can pass over the navigation light reflecting member 3, thereby better ensuring that the horizontal light output angle of the navigation light is 0 to 110 degrees.

[0062] In some embodiments, as Figure 4 shown, the ratio of the length L1 of the covered part of the navigation light reflecting member 3 to the length L2 of the un-covered part on one side is 2.8 to 3.2:1. According to the above technical solution, the integrated wing tip lighting system of the present invention can achieve the following beneficial technical effects: By the better ratio of the length of the covered part of the navigation light reflecting member 3 to the length of the un-covered part on one side, it can better ensure that the horizontal light output angle of the navigation light is 0 to 110 degrees.

[0063] Preferably, as Figure 4 shown, the length L1 of the covered part of the navigation light reflecting member 3 is 24 mm at the bottom edge; the length L2 of the un-covered part on one side of the navigation light reflecting member 3 is 8 mm.

[0064] Preferably, as Figure 4 shown, the navigation light reflecting member 3 is composed of multiple reflecting plates. The emitted light can be reflected by the reflecting member to the edge part of the navigation light dihedral angle, increasing the edge light intensity. Since the normal light distribution of the emitted light gradually weakens from the center line of the light source to both sides, a gap is left on each side of the navigation light reflecting member to ensure the basic light intensity of the dihedral angle of the red / green navigation light within the range of horizontal 0° to 110° and vertical -90° to 90°. The reflecting member extending in the middle part can reflect the light intensity of the central part to the edge area of the dihedral angle, making the light distribution more uniform.

[0065] In some embodiments, as Figure 4As shown, the two side edges of the covering part of the navigation light reflector component 3 are not perpendicular to the bottom edge of the covering part of the navigation light reflector component 3, but form an angle of 1 to 3 degrees with respect to the perpendicular line of the bottom edge. According to the above technical solution, the integrated wingtip lighting system of the present invention can achieve the following beneficial technical effects: Since the two side edges of the covering part of the navigation light reflector component 3 form an angle of 1 to 3 degrees with respect to the perpendicular line of the bottom edge, the top edge of the covering part of the navigation light reflector component 3 is slightly shortened with respect to the bottom edge (for example, preferably, the length at the top edge is 23.3 mm and the length at the bottom edge is 24 mm), the light distribution is more uniform, and it can better ensure that the horizontal light output angle of the navigation light is 0 to 110 degrees.

[0066] In some embodiments, as Figure 1 shown, the integrated wingtip lighting system further includes a lens retaining ring for pressing the anti-collision light lens 5 above the anti-collision light source printed circuit board 4 and mounting the anti-collision light lens 5 on the housing 1. According to the above technical solution, the integrated wingtip lighting system of the present invention can achieve the following beneficial technical effects: Through the appropriately arranged lens retaining ring, the anti-collision light lens 5 can be better mounted above the anti-collision light source printed circuit board 4 and on the housing 1.

[0067] In some embodiments, as Figure 1 shown, the navigation light source printed circuit board 2 adopts a dual-module design, that is, a dual-redundancy design. According to the above technical solution, the integrated wingtip lighting system of the present invention can achieve the following beneficial technical effects: Each module is powered by a different constant current drive module, and the redundant design can ensure the normal navigation of the aircraft even if a problem occurs in a single module of the red / green navigation light.

[0068] Preferably, as Figure 1 shown, the red navigation light and the green navigation light share the reflector component, and the optical design part is shared. The difference lies in the different light colors of the used LEDs. Considering the dual-redundancy design, both the red / green navigation lights adopt five LEDs in series as a module, with a total of two modules, and the two modules are powered by different constant current drive modules.

[0069] Preferably, the light output angle of the navigation light is 0° to 110°, and the light output angle of the anti-collision light is -10° to 100°. The optical path effect of the integrated wingtip lighting system emitted from the wingtip lamp cover is as Figure 5 shown.

[0070] According to an embodiment of the present invention, an aircraft includes the integrated wingtip lighting system described in any of the above aspects. According to the above technical solution, the aircraft of the present invention can achieve the following beneficial technical effects: It can reduce the size and weight of the wingtip lighting system, reduce the size of the wingtip lamp cover, and the installation positions of the navigation light and the anti-collision light make their respective light-emitting surfaces non-interfering.

[0071] The specific embodiments of the present invention have been described above. However, those skilled in the art will understand that the above specific embodiments do not constitute a limitation on the present invention. Based on the above disclosed content, those skilled in the art can make various modifications without exceeding the scope of the present invention.

Claims

1. An integrated wingtip lighting system, which includes a housing, a navigation light source printed circuit board, a navigation light reflector component, an anti-collision light source printed circuit board, and an anti-collision light lens. Among them, The navigation light source printed circuit board is installed on the first installation plane of the housing, and the anti-collision light source printed circuit board is installed on the second installation plane of the housing. The first installation plane and the second installation plane are adjacent to each other. The navigation light reflector component is installed on one side of the navigation light source printed circuit board. The first installation plane is aligned with the aircraft heading, the second installation plane forms a second installation angle of 28 - 32 degrees with the aircraft heading, the extension plane of the navigation light reflector component forms an extension angle of 26 - 30 degrees with the aircraft heading, and the anti-collision light lens is installed above the anti-collision light source printed circuit board.

2. The integrated wing tip lighting system according to claim 1, wherein The second installation angle is 30 degrees.

3. The integrated wing tip lighting system according to claim 1, wherein The extension angle is 28 degrees.

4. The integrated wingtip lighting system according to claim 1, wherein, The navigation light reflector component is in the shape of a reflector bowl.

5. The integrated wingtip lighting system according to claim 1, characterized in that, The navigation light reflector component covers the middle part of the navigation light source printed circuit board, and there are gaps on both sides of the navigation light reflector component without covering the remaining part of the navigation light source printed circuit board.

6. The integrated wingtip lighting system according to claim 5, characterized in that, The ratio of the length of the covered part of the navigation light reflector component to the length of the un-covered part on one side is 2.8 - 3.2:

1.

7. The integrated wingtip lighting system according to claim 1, characterized in that, The two sides of the covered part of the navigation light reflector component are not perpendicular to the bottom edge of the covered part of the navigation light reflector component, but form an angle of 1 - 3 degrees with respect to the perpendicular line of the bottom edge.

8. The integrated wingtip lighting system according to claim 1, characterized in that, The integrated wingtip lighting system further includes a lens retaining ring for pressing the anti-collision light lens above the anti-collision light source printed circuit board and installing the anti-collision light lens on the housing.

9. The integrated wingtip lighting system according to claim 1, wherein, The navigation light source printed circuit board adopts a dual-module design.

10. An aircraft, including the integrated wingtip lighting system according to any one of claims 1 - 9.

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