Modularized detachable aviation obstruction beacon

Abstract

The invention is suitable for the technical field of aviation obstruction lights, and provides a modularized detachable aviation obstruction light which comprises a bearing seat, an aviation obstruction light body, a self-balancing mechanism and a buffering mechanism, a mounting cavity is formed in the bearing seat, and the aviation obstruction light body is detachably connected to the top of the bearing seat in a modularized mode. The supporting rods in the self-balancing mechanism are used for supporting the bearing base and the whole aviation obstruction beacon body on the bearing base, when an uneven road surface is met, the supporting rods slide to enable the second abutting face to relatively slide on the first abutting face, meanwhile, the adjusting plate slides on the linkage plate and synchronously drives the other supporting rod to synchronously slide, and therefore the supporting base and the aviation obstruction beacon body on the supporting base are supported; the supporting seat can relatively achieve self-balancing movement during movement, the situation that the supporting seat and the aviation obstruction beacon body are integrally inclined or even toppled and damaged is avoided, and the aviation obstruction beacon body is effectively protected while simpleness and high efficiency are achieved. And the buffering and damping effects are achieved through the arrangement of the buffering mechanism.

Description

Technical Field

[0001] The present invention belongs to the technical field of aviation obstruction lights, and in particular relates to a modular and detachable aviation obstruction light. Background Art

[0002] Aviation obstruction lights, also known as navigation lighting equipment, are special lamps for marking obstacles and belong to the navigation lighting equipment industry. Aviation obstruction lights are the range of lights under it. In order to distinguish them from general-purpose lighting lamps, aviation obstruction lights are not always on but flashing. Low-intensity aviation obstruction lights are always on, while medium-intensity aviation obstruction lights and high-intensity aviation obstruction lights flash. The flashing frequency is not less than 20 times per minute and not more than 60 times per minute. The function of aviation obstruction lights is to display the outline of the structure, so that the aircraft operator can judge the height and outline of the obstacle and play a warning role.

[0003] At present, in order to prevent the aviation obstruction light from being placed directly on the ground, which may cause the bottom of the aviation obstruction light to be worn or damaged by moisture, a base is generally provided at the bottom of the aviation obstruction light, which is used for supporting, carrying and moving the aviation obstruction light.

[0004] In the related technology, although there are many kinds of aviation obstruction lights and their bases, there are still some problems. For example, in order to facilitate the transportation of aviation obstruction lights, they are generally separated from the base, and the two are transported to designated locations and then modularly assembled. After the assembly is completed, the aviation obstruction light and its base need to be moved as a whole. However, as far as the current base is concerned, most of them only have the supporting function for the aviation obstruction light. Although rollers are set at the bottom of the base, during the movement, if the road surface is not flat enough, it will cause the base to be bumpy and tilted. In severe cases, it may even cause the aviation obstruction light to topple over and be damaged as a whole. There are great safety hazards, and the aviation obstruction light cannot be kept in a relatively stable and horizontal state during the movement. Summary of the invention

[0005] The present invention provides a modular detachable aviation obstruction light, aiming to solve the problem that the base of the current aviation obstruction light cannot keep the lamp body in a relatively stable and horizontal state during movement, and is prone to bumps or even tipping over, posing a great safety hazard.

[0006] The present invention is implemented as follows: a modular detachable aviation obstruction light comprises: a supporting seat, an aviation obstruction light body, a self-balancing mechanism and a buffer mechanism, wherein a mounting cavity is provided inside the supporting seat, and the aviation obstruction light body is modularly detachably connected to the top of the supporting seat;

[0007] The self-balancing mechanism is arranged in the installation cavity of the supporting seat, and the self-balancing mechanism includes a support rod, a docking seat, a linkage plate, an adjustment plate, a chute, a first abutting surface and a second abutting surface. Through holes are provided through the four corners of the bottom of the supporting seat, the support rod is slidably connected in the through holes, the docking seat is fixed at the center of the top of the installation cavity of the supporting seat, the center of the linkage plate is rotationally connected to the docking seat through a shaft rod, the adjustment plate is arranged at one end of the linkage plate and there are two adjustment plates symmetrically arranged, the chute is provided through the adjustment plate, and the adjustment plate is slidably abutted in the chute. Both the first abutting surface and the second abutting surface are inclined plane structures, the first abutting surface is symmetrically arranged at both ends of the adjustment plate, the second abutting surface is arranged at one end of the support rod close to the adjustment plate, and the first abutting surface and the second abutting surface are slidably abutted against each other;

[0008] The buffer mechanism is arranged at one end of the support rod outside the supporting seat, and the buffer mechanism for buffering is located at the bottom of the supporting seat.

[0009] Preferably, the buffer mechanism includes a support foot, a first transmission rod and a paddle. A cavity is provided at the top of the support foot, and the support foot is slidably sleeved on one end of the support rod at the bottom of the supporting seat. A buffer cavity is provided in the support rod. The first transmission rod is rotationally connected to the axis of the buffer cavity, and one end is located in the cavity of the support foot. Damping grease is filled in the support rod, and the paddle is fixed on the first transmission rod and is located in the buffer cavity.

[0010] Preferably, the buffer mechanism further includes a driven bevel gear, a fixed seat, a second transmission rod and a driving bevel gear. The driven bevel gear is coaxially fixed on the first transmission rod and is located in the cavity of the support foot. The U-shaped fixed seat is fixed on one end of the support rod in the cavity of the support foot. The second transmission rod is rotationally connected to the fixed seat along the radial direction of the support rod. The driving bevel gear is coaxially fixed on the second transmission rod and meshes with the driven bevel gear.

[0011] Preferably, the buffer mechanism further includes a linkage gear and a rack. The linkage gear is coaxially fixed on one end of the second transmission rod. The rack is fixed on the inner wall of the cavity of the support foot along the axial direction of the support foot, and the linkage gear meshes with the rack.

[0012] Preferably, a positioning disk is coaxially fixed on the outside of the support rod, and a first reset member is sleeved on the outside of the support rod. Both the positioning disk and the first reset member are located in the installation cavity of the supporting seat, and one end of the first reset member abuts against the positioning disk and the other end abuts against the bottom of the installation cavity of the supporting seat.

[0013] Preferably, two limit frames are symmetrically fixed to both ends of the linkage plate, and the adjustment plate is slidably engaged in the limit frames.

[0014] Preferably, a ball is embedded in the abutting end of the linkage plate and the adjustment plate, and the ball rolls and abuts against the adjustment plate.

[0015] Preferably, a first protrusion is disposed at the bottom of the fixing seat and the bottom of the support leg cavity, and a second restoring member is disposed between two adjacent first protrusions.

[0016] Preferably, a roller seat is rotatably connected to the bottom axis of the support leg in a radial direction, and a walking wheel is rotatably connected to the roller seat.

[0017] Preferably, a second protrusion is fixed on the outer wall of the supporting seat, and a screw hole is provided through the second protrusion, and a threaded rod is matched with the inner thread of the screw hole of the second protrusion, and a wheel disc is coaxially fixed on the top end of the threaded rod.

[0018] Compared with the prior art, the embodiments of the present application have the following beneficial effects:

[0019] 1. The support rod in the self-balancing mechanism is used to support the support seat and the aviation obstruction light body thereon as a whole. When encountering an uneven road surface, the support rod slides to make the second abutting surface slide relatively on the first abutting surface. At the same time, the adjustment plate slides on the linkage plate and simultaneously drives the other support rod to slide synchronously, so that the support seat can achieve relative self-balancing movement when moving, avoiding the support seat and the aviation obstruction light body from tilting or even tipping over and being damaged. It is simple and efficient, and also effectively protects the aviation obstruction light body.

[0020] 2. By utilizing the setting of the buffer mechanism, the supporting seat can slide relative to the support rod during the movement, and then the first transmission rod can drive the blade to move in the buffer cavity of the support rod through other linkage components, and the damping grease in the buffer cavity hinders the movement of the blade, thereby achieving a buffering and shock-absorbing effect. At the same time, the axial rotation shock-absorbing method replaces the traditional linear extrusion buffering and shock-absorbing method, so that the buffer mechanism can be more linear and stable during buffering and shock-absorbing, thereby greatly improving the buffering and shock-absorbing effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the external overall structure of the present invention;

[0022] Figure 2 It is a schematic diagram of the supporting seat structure of the present invention;

[0023] Figure 3 It is a schematic diagram of the structure of the self-balancing mechanism of the present invention;

[0024] Figure 4 It is a schematic diagram of the adjustment plate and its connection structure of the present invention;

[0025] Figure 5 It is a schematic diagram of the connection structure of the support rod and the support foot of the present invention;

[0026] Figure 6 is a schematic diagram of the cross-sectional structure of the buffer mechanism of the present invention;

[0027] In the figure: 1. supporting seat; 2. aviation obstruction light body; 3. self-balancing mechanism; 31. support rod; 32. docking seat; 33. linkage plate; 34. adjustment plate; 35. slide groove; 36. first abutment surface; 37. second abutment surface; 38. positioning plate; 39. first reset member; 4. buffer mechanism; 41. support foot; 42. first transmission rod; 43. blade; 44. driven bevel gear; 45. fixed seat; 46. second transmission rod; 47. driving bevel gear; 48. linkage gear; 49. rack; 410. first protrusion; 411. second reset member; 5. limit frame; 6. ball; 7. walking wheel; 8. second protrusion; 9. threaded rod. DETAILED DESCRIPTION

[0028] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by technicians in the technical field of this application; the terms used in the specification of the application herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" and any variations thereof in the specification and claims of this application and the above-mentioned drawings are intended to cover non-exclusive inclusions. The terms "first", "second", etc. in the specification and claims of this application or the above-mentioned drawings are used to distinguish different objects, not to describe a specific order.

[0029] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0030] The embodiment of the present invention provides a modular detachable aviation obstruction light, such as Figure 1-6 As shown, it includes: a supporting seat 1, an aviation obstruction light body 2, a self-balancing mechanism 3 and a buffer mechanism 4. The supporting seat 1 is provided with a mounting cavity inside, and the aviation obstruction light body 2 is modularly detachably connected to the top of the supporting seat 1;

[0031] The self-balancing mechanism 3 is arranged in the installation cavity of the supporting seat 1, and the self-balancing mechanism 3 includes a support rod 31, a docking seat 32, a linkage plate 33, an adjustment plate 34, a slide groove 35, a first abutting surface 36 and a second abutting surface 37. Through holes are provided at the four corners of the bottom of the supporting seat 1, the support rod 31 is slidably connected in the through holes, the docking seat 32 is fixed at the center of the top of the installation cavity of the supporting seat 1, and the center of the linkage plate 33 is rotatably connected with the docking seat 32 through an axle rod, the adjustment plate 34 is arranged at one end of the linkage plate 33, and two are symmetrically arranged, the slide groove 35 is arranged on the adjustment plate 34, and the adjustment plate 34 slides and abuts in the slide groove 35, the first abutting surface 36 and the second abutting surface 37 are both inclined structures, and the first abutting surface 36 is symmetrically arranged at both ends of the adjustment plate 34, the second abutting surface 37 is arranged on one end of the support rod 31 close to the adjustment plate 34, and the first abutting surface 36 and the second abutting surface 37 slide and abut each other;

[0032] The buffer mechanism 4 is arranged on one end of the support rod 31 located outside the support seat 1, and the buffer mechanism 4 used for buffering is located at the bottom of the support seat 1. The buffer mechanism 4 includes a support foot 41, a first transmission rod 42 and a paddle 43. A cavity is arranged on the top of the support foot 41, and the support foot 41 is slidably sleeved on one end of the support rod 31 located at the bottom of the support seat 1, and a buffer cavity is arranged in the support rod 31. The first transmission rod 42 is rotatably connected to the axis center of the buffer cavity, and one end is located in the cavity of the support foot 41, and the support rod 31 is filled with damping grease, and the paddle 43 is fixed on the first transmission rod 42 and is located in the buffer cavity.

[0033] It should be noted that, since the base of the current aviation obstruction light cannot keep the lamp body in a relatively stable and horizontal state during movement, it is easy to cause bumps or even tipping over, which poses a great safety hazard. In order to solve this problem, a self-balancing mechanism 3 and a buffer mechanism 4 are provided in the present solution, and the support rod 31 in the self-balancing mechanism 3 is used to support the support seat 1 and the aviation obstruction light body 2 thereon as a whole. When encountering an uneven road surface, the support rod 31 slides to make the second abutting surface 37 slide relatively on the first abutting surface 36, and at the same time, the adjustment plate 34 slides on the linkage plate 33, and synchronously drives the other support rod 31 to slide synchronously, so that the support seat 1 can relatively achieve self-balancing movement during movement, thereby avoiding the support seat 1 and the aviation obstruction light body 2 from tilting or even tipping over and being damaged as a whole. This is simple and efficient, and also effectively protects the aviation obstruction light body 2.

[0034] With the buffer mechanism 4 provided, during the movement of the supporting seat 1, relative sliding between the supporting feet 41 and the supporting rod 31 enables the first transmission rod 42 to drive the paddle 43 to move within the buffer cavity of the supporting rod 31 through other linkage components. The damping grease within the buffer cavity obstructs the movement of the paddle 43, thereby achieving the buffer and shock absorption effect. Meanwhile, the axial rotation shock absorption method replaces the traditional linear extrusion buffer and shock absorption, making the buffer mechanism 4 more linear and stable during buffer and shock absorption, and significantly improving the buffer and shock absorption effect.

[0035] Specifically, in this embodiment, the solution mainly includes a supporting seat 1, an aviation obstruction light body 2, a self-balancing mechanism 3, and a buffer mechanism 4. During use, first fix the aviation obstruction light body 2 on the supporting seat 1, and then the supporting seat 1 and the aviation obstruction light body 2 as a whole can be moved. During the movement, when encountering an uneven road surface, first, relative sliding occurs between the supporting feet 41 and the supporting rod 31. Then, the rack 49 drives the linkage gear 48 to engage and link, and the second transmission rod 46 enables the driving bevel gear 47 to rotate synchronously. The driving bevel gear 47 drives the driven bevel gear 44 to engage and link, so that the first transmission rod 42 can drive the paddle 43 to move within the buffer cavity of the supporting rod 31, achieving the buffer and shock absorption effect. At the same time, when the supporting rod 31 slides, the second abutting surface 37 slides relative to the first abutting surface 36. At this time, the adjusting plate 34 slides on the linkage plate 33 and synchronously drives another supporting rod 31 to slide synchronously, enabling the supporting seat 1 to relatively achieve self-balanced movement during movement.

[0036] In a further preferred embodiment of the present invention, as Figure 1-6 shown, the buffer mechanism 4 further includes a driven bevel gear 44, a fixed seat 45, a second transmission rod 46, and a driving bevel gear 47. The driven bevel gear 44 is coaxially fixed on the first transmission rod 42 and is located within the cavity of the supporting foot 41. The U-shaped fixed seat 45 is fixed at one end of the supporting rod 31 within the cavity of the supporting foot 41. The second transmission rod 46 is rotatably connected to the fixed seat 45 along the radial direction of the supporting rod 31. The driving bevel gear 47 is coaxially fixed on the second transmission rod 46 and meshes with the driven bevel gear 44.

[0037] In this embodiment, the rotation of the driving bevel gear 47 enables the driven bevel gear 44 to engage and link, and then the driven bevel gear 44 drives the first transmission rod 42 and the paddle 43 as a whole to rotate.

[0038] In a further preferred embodiment of the present invention, as Figure 1-6 shown, the buffer mechanism 4 further includes a linkage gear 48 and a rack 49. The linkage gear 48 is coaxially fixed at one end of the second transmission rod 46. The rack 49 is axially fixed on the inner wall of the cavity of the supporting foot 41, and the linkage gear 48 meshes with the rack 49.

[0039] In this embodiment, the linkage gear 48 can be synchronously meshed and linked by the movement of the rack 49, thereby driving the second transmission rod 46 to rotate.

[0040] In a further preferred embodiment of the present invention, Figure 1-6 As shown, a positioning plate 38 is coaxially fixed to the outside of the support rod 31, and a first reset member 39 is sleeved on the outside of the support rod 31. The positioning plate 38 and the first reset member 39 are both located in the mounting cavity of the support seat 1, and one end of the first reset member 39 abuts against the positioning plate 38, and the other end abuts against the bottom of the mounting cavity of the support seat 1.

[0041] In this embodiment, the support rod 31 is pushed by the elastic force of the first restoring member 39 so that the first abutting surface 36 and the second abutting surface 37 can always abut against each other.

[0042] In a further preferred embodiment of the present invention, Figure 1-6 As shown, two limit frames 5 are symmetrically fixed at both ends of the linkage plate 33 , and the adjustment plate 34 is slidably engaged in the limit frames 5 .

[0043] In this embodiment, the regulating plate 34 is limited by the limiting frame 5 to prevent it from being separated from the linkage plate 33 .

[0044] In a further preferred embodiment of the present invention, Figure 1-6 As shown, the abutting ends of the linkage plate 33 and the adjustment plate 34 are embedded with balls 6 , and the balls 6 are in rolling abutment with the adjustment plate 34 .

[0045] In this embodiment, the friction resistance between the linkage plate 33 and the adjustment plate 34 is reduced by the rolling of the balls 6 , so that the adjustment plate 34 can slide quickly on the linkage plate 33 .

[0046] In a further preferred embodiment of the present invention, Figure 1-6 As shown, the bottom of the fixing seat 45 and the bottom of the cavity of the support leg 41 are both provided with a first protrusion 410 , and a second restoring member 411 is provided between two adjacent first protrusions 410 .

[0047] In this embodiment, the second restoring member 411 enables the support leg 41 to be quickly restored on the support rod 31 .

[0048] In a further preferred embodiment of the present invention, Figure 1-6 As shown, a roller seat is rotatably connected to the bottom axis of the support leg 41 in a radial direction, and a running wheel 7 is rotatably connected to the roller seat.

[0049] In this embodiment, the arrangement of the running wheels 7 enables the entire device to be quickly moved to a suitable position for use.

[0050] In a further preferred embodiment of the present invention, Figure 1-6 As shown, a second protrusion 8 is fixed on the outer wall of the supporting seat 1, and a screw hole is provided through the second protrusion 8, and a threaded rod 9 is matched with the inner thread of the screw hole of the second protrusion 8, and a wheel disc is coaxially fixed on the top of the threaded rod 9.

[0051] In this embodiment, the threaded rod 9 is rotated to engage with the threads in the screw hole, so that one end of the threaded rod 9 can abut against the ground, thereby achieving a locking effect on the supporting seat 1 to prevent it from moving during use.

[0052] It should be noted that, for the above-mentioned embodiments, for the sake of simplicity, they are all described as a series of action combinations, but those skilled in the art should know that the present invention is not limited by the described order of actions, because according to the present invention, some steps may be performed in other orders or simultaneously. Secondly, those skilled in the art should also know that the embodiments described in the specification are all preferred embodiments, and the actions and modules involved are not necessarily required by the present invention.

[0053] In the several embodiments provided in the present application, it should be understood that the disclosed devices can be implemented in other ways. For example, the device embodiments described above are merely schematic, such as the division of the above-mentioned units. There may be other division methods in actual implementation, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or communication connection shown or discussed can be through some interfaces, and the indirect coupling or communication connection between devices or units can be in the form of telecommunication or other forms.

[0054] The units described above as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0055] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the scope of protection of the invention. Obviously, the described embodiments are only some embodiments of the present invention, rather than all embodiments. Based on these embodiments, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention. Although the present invention has been described in detail with reference to the above embodiments, ordinary technicians in this field can still combine, add, delete or make other adjustments to the features in the various embodiments of the present invention according to the circumstances without conflict, without making creative work, so as to obtain different other technical solutions that do not deviate from the concept of the present invention in essence, and these technical solutions also belong to the scope of protection of the present invention.

Claims

1. A modular detachable aviation obstruction light, characterized in that: Including: A supporting base (1), an aviation obstruction lamp body (2), a self-balancing mechanism (3) and a buffer mechanism (4). An installation cavity is provided inside the supporting base (1), and the aviation obstruction lamp body (2) is detachably connected to the top of the supporting base (1) in a modular manner; The self-balancing mechanism (3) is arranged in the installation cavity of the supporting base (1), and the self-balancing mechanism (3) includes a support rod (31), a docking seat (32), a linkage plate (33), an adjustment plate (34), a chute (35), a first abutting surface (36) and a second abutting surface (37). Through holes are provided at the four corners of the bottom of the supporting base (1), and the support rod (31) is slidably connected in the through holes. The docking seat (32) is fixed at the center of the top of the installation cavity of the supporting base (1). The center of the linkage plate (33) is rotatably connected to the docking seat (32) through a shaft rod. The adjustment plate (34) is arranged at one end of the linkage plate (33) and there are two symmetrically. The chute (35) is provided through the adjustment plate (34), and the adjustment plate (34) is slidably abutted in the chute (35). Both the first abutting surface (36) and the second abutting surface (37) are inclined surface structures. The first abutting surface (36) is symmetrically arranged at both ends of the adjustment plate (34). The second abutting surface (37) is arranged at one end of the support rod (31) close to the adjustment plate (34), and the first abutting surface (36) and the second abutting surface (37) are slidably abutted against each other; The buffer mechanism (4) is arranged at one end of the support rod (31) outside the supporting base (1), and the buffer mechanism (4) for buffering is located at the bottom of the supporting base (1).

2. A modular detachable aviation obstruction light as claimed in claim 1, characterized in that: The buffer mechanism (4) includes a support leg (41), a first transmission rod (42) and a paddle (43). A cavity is provided at the top of the support leg (41), and the support leg (41) is slidably sleeved on one end of the support rod (31) at the bottom of the supporting base (1). A buffer cavity is provided in the support rod (31). The first transmission rod (42) is rotatably connected to the axis of the buffer cavity, and one end is located in the cavity of the support leg (41). Damping grease is filled in the support rod (31). The paddle (43) is fixed on the first transmission rod (42) and is located in the buffer cavity.

3. A modular detachable aviation obstruction light as claimed in claim 2, characterized in that: The buffer mechanism (4) further includes a driven bevel gear (44), a fixing seat (45), a second transmission rod (46) and a driving bevel gear (47). The driven bevel gear (44) is coaxially fixed on the first transmission rod (42) and is located in the cavity of the support leg (41). The fixing seat (45) with a U-shaped structure is fixed on one end of the support rod (31) located in the cavity of the support leg (41). The second transmission rod (46) is rotatably connected to the fixing seat (45) along the radial direction of the support rod (31). The driving bevel gear (47) is coaxially fixed on the second transmission rod (46) and meshes with the driven bevel gear (44).

4. A modular detachable aviation obstruction light as claimed in claim 3, characterized in that: The buffer mechanism (4) further comprises a linkage gear (48) and a rack (49); the linkage gear (48) is coaxially fixed to one end of the second transmission rod (46); the rack (49) is axially fixed to the inner wall of the cavity of the support foot (41) along the support foot (41); and the linkage gear (48) and the rack (49) are meshed.

5. The modular detachable aviation obstruction light according to claim 1, characterized in that: A positioning plate (38) is coaxially fixed to the outside of the support rod (31), and a first reset member (39) is sleeved on the outside of the support rod (31). The positioning plate (38) and the first reset member (39) are both located in the mounting cavity of the support seat (1), and one end of the first reset member (39) abuts against the positioning plate (38), and the other end abuts against the bottom of the mounting cavity of the support seat (1).

6. A modular detachable aviation obstruction light as claimed in claim 1, characterized in that: Two limit frames (5) are symmetrically fixed at both ends of the linkage plate (33), and the adjustment plate (34) is slidably engaged in the limit frames (5).

7. The modular detachable aviation obstruction light according to claim 1, characterized in that: A ball (6) is embedded in the abutting end of the linkage plate (33) and the adjustment plate (34), and the ball (6) rolls and abuts against the adjustment plate (34).

8. The modular detachable aviation obstruction light according to claim 3, characterized in that: The bottom of the fixing seat (45) and the bottom of the cavity of the supporting foot (41) are both provided with a first protrusion (410), and a second restoring member (411) is provided between two adjacent first protrusions (410).

9. A modular detachable aviation obstruction light as claimed in claim 2, characterized in that: A roller seat is rotatably connected to the bottom axis of the support leg (41) in the radial direction, and a running wheel (7) is rotatably connected to the roller seat.

10. The modular detachable aviation obstruction light according to claim 1, characterized in that: A second protrusion (8) is fixed on the outer wall of the supporting seat (1), and a screw hole is provided through the second protrusion (8). The inner thread of the screw hole of the second protrusion (8) is matched with a threaded rod (9), and a wheel disc is coaxially fixed on the top end of the threaded rod (9).

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