Retractable landing lamp and manufacturing process thereof

Abstract

The invention provides a retractable landing lamp and a manufacturing process thereof, and relates to the technical field of landing lamps, and the retractable landing lamp comprises an LED light source, a rotary support, a gear assembly, a driving assembly, a pin shaft and a housing. The gear assembly comprises a power mechanism and a multi-stage speed reduction mechanism which are arranged in the first shell, and the driving assembly comprises a driving circuit arranged in the second shell. The first shell and the second shell are detachably connected and jointly define a rotating space, the pin shaft penetrates through the two shells and the rotary support to enable the pin shaft to be rotatably supported in the space, and a final-stage output gear of the multi-stage speed reduction mechanism is meshed with a tooth-shaped structure on the arc-shaped outer edge of the rotary support. The rotary support is driven by the multi-stage transmission mechanism to rotate around the pin shaft, electric adjustment of the LED light source in the range of 0-90 degrees in the vertical direction and hovering at any angle are achieved, the technical problem that the irradiation direction of a traditional fixed landing lamp cannot be adjusted is effectively solved, and the illumination adaptability and safety of an airplane under different take-off and landing conditions are remarkably improved.

Description

TECHNICAL FIELD

[0001] The present application mainly relates to the technical field of landing lights, in particular to a retractable landing light and a manufacturing process thereof. BACKGROUND

[0002] A landing light is a key lighting device for an aircraft during the take-off and landing phase, which is used to illuminate the runway and provide a clear view for the pilot to ensure flight safety. With the continuous progress of aviation technology, aircraft systems have higher requirements for onboard devices, especially in the lighting field. Not only do they need to have high reliability, low power consumption, and easy disassembly and maintenance, but they also need to have a flexible and adjustable illumination direction to adapt to complex and variable take-off and landing environments.

[0003] However, most of the currently widely used onboard landing lights use a fixed installation structure, and their illumination angle is determined after installation and cannot be adjusted according to actual needs. This fixed illumination mode has obvious limitations: on the one hand, it cannot flexibly adjust the light beam direction for different aircraft models and different take-off and landing conditions, affecting the optimization of the lighting effect; on the other hand, in the non-use state, the landing light is usually exposed and is easily affected by the external environment, increasing the risk of damage and being not conducive to the aerodynamic shape of the aircraft.

[0004] Therefore, the traditional landing light does not have the self-adjusting ability of the illumination direction and cannot meet the use requirements of modern aircraft for the functional diversification and intelligent control of the light system. SUMMARY

[0005] 1. Technical problems to be solved by the present application: The present application provides a retractable landing light and a manufacturing process thereof to solve the technical problems in the background.

[0006] 2. Technical solutions: To achieve the above-mentioned purpose, the technical solutions provided by the present application are as follows: a retractable landing light, comprising an LED light source; a rotary support fixedly connected with the LED light source; a gear assembly comprising a first housing and a power mechanism and a multi-stage reduction mechanism arranged in the first housing; a drive assembly comprising a second housing and a drive circuit arranged in the second housing; The first housing and the second housing are detachably connected and jointly define a rotation space; a pin shaft penetrating through the first housing, the rotary support and the second housing, so that the rotary support is rotatably supported in the rotation space; The last stage output gear of the multi-stage reduction mechanism is engaged with a toothed structure arranged on the arc-shaped outer edge of the rotary support; A cover is fixedly connected with the first and second shells and is provided with a fuselage mounting interface.

[0007] The device driving assembly comprises a second shell in which a driving circuit board is mounted, which is responsible for providing power for the motor and LED light source and power mechanism and processing control signals. The first shell and the second shell are detachably connected by screws. When the two are combined, a clear rotation space is defined at the joint. The fuselage mounting interface of the cover is used to securely mount the entire landing light to the skin of the aircraft belly. In operation, the driving circuit receives instructions from the aircraft control system and drives the power mechanism to rotate. The power of the power mechanism is transmitted step by step through a multi-stage reduction mechanism and the torque is amplified. Finally, the last-stage output gear drives the rotary support engaged with it. The rotary support rotates around the pin shaft in the rotation space defined by the first and second shells, thereby driving the LED light source to adjust and hover at any angle within the range of zero to ninety degrees vertically. When the landing light is not in use, it can be controlled to retract to the position close to the cover. The top of the LED light source is provided with a rubber ring to achieve buffering and sealing, thereby achieving optimal protection. The device successfully achieves electric stepless adjustment and precise hovering of the landing light within the range of zero to ninety degrees vertically through the innovative gear transmission and rotary support structure, completely overcoming the drawbacks of the fixed landing light that cannot adjust the illumination direction, greatly enhancing the lighting adaptability of the aircraft in different take-off and landing environments. An angle sensor can be provided on the side of the rotary support to facilitate adjustment to a specific angle. The angle sensor uses existing technology and will not be described here.

[0008] Further, the power mechanism is an electric motor, and the multi-stage reduction mechanism comprises at least: a first reduction unit comprising a first worm and a first turbine engaged with the output shaft of the power mechanism, both of which have vertical teeth; a second reduction unit comprising a second worm and a second turbine engaged with the first turbine, both of which have vertical teeth; a transmission unit comprising a rotating shaft coaxially arranged with the second turbine, one end of the rotating shaft being rotatably connected to the second shell, and the rotating shaft further comprising the last-stage output gear and the tooth structure of the rotary support engaged with each other.

[0009] Further, the output shaft end of the power mechanism is annularly provided with a connecting groove, and one end of the first worm is sleeved in the connecting groove and fixed coaxially by a compression screw.

[0010] Further, the first turbine is clamped on the second worm to achieve coaxial linkage, and the top and bottom of the second worm are rotatably connected to a support seat, and the support seat is detachably connected to the inner wall of the first shell by a bolt.

[0011] Further, one end of the rotating shaft is rotatably connected to the outer sidewall of the second shell, and the middle part of the rotating shaft is further rotatably connected to a shaft rod end cover, and the shaft rod end cover is connected to the first shell by bolts.

[0012] Further, the swivel support comprises an integrally formed arc-shaped plate segment and a connecting plate segment; the outer arc surface of the arc-shaped plate segment is provided with a continuous tooth-shaped structure for meshing with the final-stage output gear; the arc-shaped plate segment is connected to a rotating sleeve through a transition connecting column, and the rotating sleeve is supported on the pin shaft through a bearing; the connecting plate segment extends from the arc-shaped plate segment, and the distal end thereof is provided with a mounting interface for detachably connecting to the sidewall of the LED light source through fasteners.

[0013] Further, the driving assembly further comprises an electrical connector, and the driving circuit is electrically connected to the electrical connector, the LED light source and the motor in the gear assembly through wires.

[0014] And a manufacturing process of the retractable landing light comprises the following steps: Gear assembly assembly step: assembling the motor, the first worm, the first turbine, the second worm, the second turbine, the final-stage output gear and corresponding bearings and end covers in the first shell to form the gear assembly; Driving assembly assembly step: installing the driving circuit and the electrical connector in the second shell to form the driving assembly; Overall assembly step: fixing the LED light source to the swivel support; placing the swivel support in the rotating space formed after the first shell and the second shell are folded, and connecting through the pin shaft; fixing the gear assembly and the driving assembly to the cover and connecting them to each other; and completing the connection of all electrical circuits.

[0015] And an aircraft is provided with the retractable landing light.

[0016] 3. Beneficial effects: Compared with the prior art, the technical scheme provided by the present application has the following beneficial effects: The present application has a reasonable design, and through the cooperation of the innovative multi-stage speed reduction transmission mechanism and the swivel support, the electric stepless adjustment and accurate hovering of the landing light irradiation angle in the range of 0° to 90° are realized, and the technical problem of the fixed landing light irradiation direction being unadjustable is completely solved, and the lighting adaptability of the aircraft under different take-off and landing conditions is significantly improved.

[0017] The worm and gear transmission combination has the advantages of stable transmission, low noise and reliable self-locking, and ensures that the lighting unit stably hovers at any position. The modular shell design and detachable connection structure make the product have the characteristics of easy assembly and easy maintenance, and effectively reduce the life cycle maintenance cost.

[0018] The overall structure meets the requirements of light weight and high strength, cooperates with the low power consumption characteristics of the LED light source, meets the strict standards of reliability and environmental adaptability of aviation equipment, and provides a high-performance solution for the lighting system of a modern aircraft.

[0019] It should be noted that the structures not introduced in the present application do not involve the design points and improvement direction of the present application, are the same as the prior art or can be realized by using the prior art, and are not described here. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 is a structural schematic diagram of the present application; Figure 2 is a structural schematic diagram of the present application from another angle; Figure 3 is a structural schematic diagram of the present application when the second shell is disassembled; Figure 4 is a structural schematic diagram of the present application when the first shell is disassembled; Figure 5 is a structural schematic diagram of the present application when the first shell is opened on one side; Figure 6 is a schematic diagram of the present application when the LED light source is rotated by a certain angle; Figure 7 is a structural schematic diagram of the multi-stage speed reduction mechanism of the present application; Figure 8 is a structural schematic diagram of the present application Figure 7 is an enlarged schematic diagram of the structure at A of the present application.

[0021] Reference signs: 1, LED light source; 2, rotary support; 21, arc plate section; 22, connecting plate section; 23, toothed structure; 24, transition connecting column; 25, rotating sleeve; 3, first shell; 4, power mechanism; 5, multi-stage speed reduction mechanism; 51, first worm; 52, first turbine; 53, second worm; 531, support seat; 54, second turbine; 55, rotating shaft; 551, shaft rod end cover; 9, final stage output gear; 6, second shell; 7, drive circuit; 71, electrical connector; 8, pin shaft; 10, cover. DETAILED DESCRIPTION

[0022] In order to facilitate the understanding of the present application, the present application will be described more fully below with reference to the related drawings, which show several embodiments of the present application. However, the present application can be realized in many different forms and is not limited to the embodiments described herein. On the contrary, the purpose of providing these embodiments is to make the disclosure of the present application more thorough and comprehensive.

[0023] In the description of the present application, it needs to be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "page", "bottom", "inner", "outer", "clockwise", "counterclockwise" and the like indicate the orientation or positional relationship shown in the drawings, which are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0024] In addition, the terms "first", "second" are only for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features referred to. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "multiple" is two or more, unless otherwise specifically limited.

[0025] In the present application, unless otherwise specifically defined and limited, the terms "mounting", "connecting", "connecting", "fixing", "providing", "provided with" and the like should be broadly understood, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0026] It should be noted that the structures not introduced in the present application do not involve the design points and improvement direction of the present application, and can adopt the existing technology known to those skilled in the art.

[0027] The specific implementation of the present application is described in detail below in combination with specific embodiments.

[0028] Referring to the drawings Figures 1-7 A retractable landing light, comprising an LED light source 1; A rotary support 2 is fixedly connected with the LED light source 1; A gear assembly comprising a first housing 3 and a power mechanism 4 and a multi-stage reduction mechanism 5 arranged therein; A drive assembly comprising a second housing 6 and a drive circuit 7 arranged therein; The first housing 3 and the second housing 6 are detachably connected and jointly define a rotation space; A pin shaft 8 penetrates the first housing 3, the rotary support 2 and the second housing 6, so that the rotary support 2 is rotatably supported in the rotation space; The final output gear 9 of the multi-stage reduction mechanism 5 meshes with the tooth structure 23 located on the arc-shaped outer edge of the rotary support 2; The cover 10 is fixedly connected to the first housing 3 and the second housing 6, and is provided with a body mounting interface.

[0029] In this embodiment, the drive assembly includes a second housing 6, inside which a drive circuit board 7 is installed. This circuit board provides power to the motor, LED light source 1, and power mechanism 4, and processes control signals. The first housing 3 and the second housing 6 are detachably connected by screws. When they are combined, their joint defines a clear rotation space. The fuselage mounting interface of the cover 10 is used to securely mount the entire landing light to the skin of the aircraft fuselage. During operation, the drive circuit 7 receives commands from the aircraft control system and drives the power mechanism 4 to rotate. The power of the power mechanism 4 is transmitted and amplified step by step through a multi-stage reduction mechanism 5, and finally driven by the final output gear 9 to drive the rotating bracket 2 that meshes with it. The rotating bracket 2 rotates precisely within the rotation space defined by the first housing 3 and the second housing 6, with the pin 8 as its axis, thereby enabling the LED light source 1 to be adjusted and hovered at any angle within the vertical range of zero to ninety degrees. When the landing light is not in use, it can be controlled to retract to a position close to the housing 10. The top of the LED light source 1 is equipped with a rubber ring for buffering and sealing, providing optimal protection. Through innovative gear transmission and rotating bracket 2 structure, this device successfully achieves electric stepless adjustment and precise hovering of the landing light illumination angle within the vertical range of zero to ninety degrees. This completely overcomes the drawback of the non-adjustable illumination direction of traditional fixed landing lights, greatly enhancing the aircraft's lighting adaptability in different take-off and landing environments. An angle sensor can be installed on the side of the rotating bracket 2 for easy adjustment to a specific angle. The angle sensor uses existing technology, which will not be described in detail here.

[0030] The power mechanism 4 is a motor, and the multi-stage reduction mechanism 5 includes at least: The first-stage reduction unit comprises a first worm 51 connected to the output shaft of the power mechanism 4 and a meshing first turbine 52, the teeth of which mesh perpendicularly. The secondary reduction unit consists of a second worm 53 coaxially arranged with the first turbine 52 and a meshing second turbine 54, with their teeth meshing perpendicularly. The transmission unit includes a rotating shaft 55 coaxially arranged with the second turbine 54. One end of the rotating shaft 55 is rotatably connected to the second housing 6. The middle part of the rotating shaft 55 is also provided with the final stage output gear 9 meshing with the tooth structure 23 of the rotary support 2. In this embodiment, the drive circuit 7 starts the motor after receiving the control command, and the motor output power is transmitted through the first and second stage reduction mechanisms. The specific transmission path is as follows: the motor drives the first worm 51 to rotate, driving the first turbine 52 to achieve first-stage reduction; the second worm 53, which is coaxial with the first turbine 52, rotates accordingly, driving the second turbine 54 to achieve second-stage reduction; the rotating shaft 55, which is coaxial with the second turbine 54, drives the final stage output gear 9 to rotate, ultimately driving the rotary support 2 to achieve the rotation operation of the rotary support 2. Through this multi-stage transmission method, the rotary support 2 can achieve precise angle adjustment within the range of zero to ninety degrees and reliably hover at any position. When the landing light is not in use, the lighting unit can be retracted to the housing 10 position by controlling the motor. At this time, the sealing ring on the top of the LED light source 1 forms soft contact with the inner wall of the housing 10, which not only serves as a limit but also provides good sealing protection. The second worm 53 is vertically set inside the first housing 3, and its two ends are rotatably connected to the inner wall of the first housing 3.

[0031] The output shaft of the power mechanism 4 has a connecting groove on its end. After one end of the first worm gear 51 is sleeved into the connecting groove, it is coaxially fixed by a clamping screw. In this embodiment, the first worm gear 51 is detachably connected to the power mechanism 4, which facilitates subsequent maintenance and replacement.

[0032] The first turbine 52 is engaged with the second worm gear 53 to achieve coaxial linkage. The top and bottom of the second worm gear 53 are rotatably connected to a support base 531. The support base 531 is detachably connected to the inner wall of the first housing 3 by bolts. In this embodiment, the first turbine 52 and the second worm gear 53 are coaxially connected using a specific engagement structure. This engagement structure includes mutually cooperating protrusions and grooves to ensure that the two rotate synchronously during transmission and facilitate accurate positioning during assembly. As a key component in the transmission chain, the second worm gear 53 is supported at both ends by precision bearings in a specially designed support base 531. Under the precise constraint of the support base 531, the second worm gear 53 maintains stable rotation and efficiently transmits power to the subsequent transmission mechanism through reliable meshing with the second turbine 54. The close cooperation between the various transmission components ensures the smooth operation of the system and provides a reliable guarantee for the precise deployment and retraction of the landing light.

[0033] One end of the rotating shaft 55 is rotatably connected to the outer wall of the second housing 6, and the middle of the rotating shaft 55 is also rotatably connected to a shaft end cap 551. The shaft end cap 551 is bolted to the first housing 3. In this embodiment, an independent shaft end cap 551 is provided at the middle position of the rotating shaft 55. The shaft end cap 551 has a second bearing embedded in it, providing a key intermediate support point for the rotating shaft 55. This shaft end cap 551 is firmly fixed to the inner cavity of the first housing 3 by fasteners. By providing support points on the two housings, a stable constraint is formed on the rotating shaft 55, ensuring the positional accuracy of the rotating shaft 55 line during transmission.

[0034] The rotary support 2 includes an integrally formed arc-shaped plate segment 21 and a connecting plate segment 22. The outer arc surface of the arc-shaped plate segment 21 is provided with a continuous tooth structure 23 for meshing with the final stage output gear 9. The arc-shaped plate segment 21 is connected to the rotating sleeve 25 through a transition connecting column 24, and the rotating sleeve 25 is supported on the pin shaft 8 by a bearing. The connecting plate segment 22 extends from the arc-shaped plate segment 21, and its end is provided with a mounting interface for detachable connection with the side wall of the LED light source 1 through fasteners. In this embodiment, the rotary support 2, as a key component connecting the lighting unit and the transmission system, has a carefully designed structure. The rotary support 2 is manufactured using an integral molding process, ensuring the overall structural strength and dimensional stability. Its main body includes two main parts: the arc-shaped plate segment 21 and the connecting plate segment 22. The arc-shaped plate segment 21 is an arc with a specific radius of curvature, and a continuous tooth structure 23 is precisely machined on its outer arc surface. These tooth profiles precisely mesh with the final output gear 9 in the transmission system, converting rotational motion into the oscillation of the rotary support 2. The arc-shaped plate segment 21 is smoothly connected to the rotating sleeve 25 via a transition connection. The rotating sleeve 25 contains sliding or rolling bearings, allowing it to rotate smoothly around the pin 8. The connecting plate segment 22 extends from one end of the arc-shaped plate segment 21, with a flat mounting interface at its end, featuring standard threaded holes. Using matching fasteners, the LED light source 1 can be securely mounted on this mounting interface. This detachable connection method ensures ease of assembly and facilitates subsequent maintenance and replacement.

[0035] The drive assembly also includes an electrical connector 71. The drive circuit 7 is electrically connected to the electrical connector 71, the LED light source 1, and the motor in the gear assembly via wires. In this embodiment, the electrical connector 71 serves as the electrical interface between the entire landing light and the external aircraft system. It is fixedly installed on the outer or inner side of the drive housing at a reserved position. Its model and interface type are compatible with the power supply and control signal standards of the aircraft platform.

[0036] The drive circuit 7, serving as the control core, is typically a printed circuit board that integrates a power management module, a motor drive chip, and a control logic unit. This circuit board is securely mounted within the drive housing using standard brackets and fasteners to prevent loosening due to vibration.

[0037] And a manufacturing process for a retractable landing light, including the following steps: Gear assembly steps: Assemble the motor, first worm 51, first turbine 52, second worm 53, second turbine 54, final stage output gear 9, and corresponding bearings and end caps into the first housing 3 to form the gear assembly. During installation, pay attention to the meshing between the various worms and turbines. Install gradually using snap-fit ​​and bolt connections. First, connect the rotating shaft 55 to the first housing 3 via the shaft end cap 551. Then, connect and fix the corresponding final stage output gear 9 and second turbine 54 to the rotating shaft 55 before rotatably connecting them to the second housing 6 on the side. Finally, use symmetrically arranged support seats 531 to support the second worm. 53 is fixed, and the first turbine 52 on the second worm 53 must mesh with the second turbine 54. Finally, after the first worm 51 and the first turbine 52 are meshed, they are threaded to the output end of the motor. After installation, when the output end is working, it will drive the first worm 51 to rotate. Then the first worm 51 drives the first turbine 52 to rotate. The second worm 53, which is coaxial with the first turbine 52, rotates. The second worm 53 drives the second turbine 54 to rotate, which in turn causes the second worm 53 on the second turbine 54 to rotate, driving the entire rotating shaft 55 to rotate. After the rotating shaft 55 rotates, it can drive the final stage output gear 9 and the reinstallation bracket to work. Drive assembly assembly steps: Install the drive circuit 7 and the electrical connector 71 into the second housing 6 to form the drive assembly; Overall assembly steps: Fix the LED light source 1 to the rotating bracket 2; place the rotating bracket 2 in the rotation space formed by the first housing 3 and the second housing 6 after they are closed, and connect them with a pin 8; fix the gear assembly and drive assembly to the cover 10 and connect them to each other; complete the connection of all electrical circuits.

[0038] This application also protects an aircraft equipped with the aforementioned retractable landing light.

[0039] The above-described embodiments are merely illustrative of certain implementations of the present invention, and are described in a relatively specific and detailed manner. However, they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements are all within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the appended claims.

Claims

1. A retractable landing light, characterized in that: include LED light source (1); The rotating bracket (2) is fixedly connected to the LED light source (1); The gear assembly includes a first housing (3) and a power mechanism (4) and a multi-stage reduction mechanism (5) disposed therein. The drive assembly includes a second housing (6) and a drive circuit (7) disposed therein. The first housing (3) and the second housing (6) are detachably connected and together define a rotation space; A pin (8) passes through the first housing (3), the rotary support (2) and the second housing (6), so that the rotary support (2) is rotatably supported in the rotation space; The final output gear (9) of the multi-stage reduction mechanism (5) meshes with the tooth structure (23) located on the arc-shaped outer edge of the rotary support (2); The cover (10) is fixedly connected to the first housing (3) and the second housing (6), and is provided with a body mounting interface.

2. A retractable landing light according to claim 1, characterized in that: The power mechanism (4) is a motor, and the multi-stage reduction mechanism (5) includes at least: The first-stage reduction unit consists of a first worm (51) connected to the output shaft of the power mechanism (4) and a meshing first turbine (52), the teeth of which mesh perpendicularly. The secondary reduction unit consists of a second worm (53) coaxially arranged with the first turbine (52) and a meshing second turbine (54), with their teeth meshing perpendicularly. The transmission unit includes a rotating shaft (55) coaxially arranged with the second turbine (54). One end of the rotating shaft (55) is rotatably connected to the second housing (6). The middle part of the rotating shaft (55) is also provided with the final stage output gear (9) meshing with the tooth structure (23) of the rotary support (2).

3. A retractable landing light according to claim 2, characterized in that: The output shaft of the power mechanism (4) has a connecting groove on its end. After one end of the first worm (51) is sleeved into the connecting groove, it is coaxially fixed by a clamping screw.

4. A retractable landing light according to claim 2, characterized in that: The first turbine (52) is snapped onto the second worm (53) to achieve coaxial linkage. The top and bottom of the second worm (53) are rotatably connected to the support seat (531), and the support seat (531) is detachably connected to the inner wall of the first housing (3) by bolts.

5. A retractable landing light according to claim 2, characterized in that: One end of the rotating shaft (55) is rotatably connected to the outer wall of the second housing (6), and the middle part of the rotating shaft (55) is also rotatably connected to the shaft end cap (551). The shaft end cap (551) is connected to the first housing (3) by bolts.

6. A retractable landing light according to claim 2, characterized in that: The rotating bracket (2) includes an integrally formed arc-shaped plate segment (21) and a connecting plate segment (22); the outer arc surface of the arc-shaped plate segment (21) is provided with a continuous tooth structure (23) for meshing with the final stage output gear (9); the arc-shaped plate segment (21) is connected to the rotating sleeve (25) through a transition connecting column (24), and the rotating sleeve (25) is supported on the pin shaft (8) by a bearing; the connecting plate segment (22) extends out from the arc-shaped plate segment (21), and its end is provided with an installation interface to achieve a detachable connection with the side wall of the LED light source (1) through fasteners.

7. A retractable landing light according to claim 1, characterized in that: The drive assembly also includes an electrical connector (71), and the drive circuit (7) is electrically connected to the electrical connector (71), the LED light source (1), and the motor in the gear assembly via wires.

8. A manufacturing process for a retractable landing light, used to manufacture the retractable landing light according to any one of claims 1-7, characterized in that, Includes the following steps: Gear assembly assembly steps: Assemble the motor, first worm (51), first turbine (52), second worm (53), second turbine (54), final stage output gear (9) and corresponding bearings and end caps into the first housing (3) to form the gear assembly; Driving component assembly steps: Install the driving circuit (7) and the electrical connector (71) into the second housing (6) to form the driving component; Overall assembly steps: Fix the LED light source (1) to the rotating bracket (2); place the rotating bracket (2) in the rotation space formed by the first housing (3) and the second housing (6) after they are closed, and connect them through with a pin (8); fix the gear assembly and the drive assembly to the cover (10) and connect them to each other; complete the connection of all electrical circuits.

9. An aircraft, characterized in that, It is equipped with a retractable landing light as described in any one of claims 1-7.

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