A multi-functional fixed-wing unmanned aerial vehicle catapult

Abstract

This invention relates to the field of UAV catapult technology, specifically to a multifunctional fixed-wing UAV catapult, comprising a catapult box, a catapult plate, an auxiliary mechanism, a crossbar, a catapult block, a first spring, and a buffer pad. The catapult block has a locking groove on its top and abutment blocks on both sides. The catapult box has through holes on both sides. The auxiliary mechanism includes a locking element, two transmission elements, a belt body, and a motor. The transmission elements include a push plate and a first screw. The push plate has a first threaded groove, and one end of the first screw has a pulley. Two support blocks are provided on both sides of the catapult box, and a limit rod is provided between the two support blocks. The motor drives the belt body to transmit power to the two first screws, thereby pushing the two push plates against the two abutment blocks, which in turn moves the catapult block towards the first spring, compressing the first spring and securing it with the locking element. This effectively reduces the user's workload.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) catapult technology, and more particularly to a multifunctional fixed-wing UAV catapult. Background Technology

[0002] Aerial photography is currently the most widespread application of drones. When drones take off, the main method is catapult takeoff, which requires a catapult. Among the existing catapults, there are two main types: aerodynamic and spring-loaded takeoff. Aerodynamic catapults have complex structures and are more expensive, so most aerial photography drones use the spring-loaded takeoff method. Existing drone launchers only provide a launch platform and are relatively bulky. Different launch directions require moving and placing the launcher, which consumes a lot of manpower.

[0003] Existing patent CN210822813U discloses a novel catapult for a fixed-wing unmanned aerial vehicle (UAV), comprising a base plate, a first motor fixedly installed inside the base plate, the output shaft of the first motor located on the upper surface of the base plate, a placement plate fixedly connected to the top of the first motor output shaft, a rotating shaft fixedly installed on one side of the upper surface of the placement plate, and a catapult plate hinged to the upper surface of the placement plate via the rotating shaft; by setting up a first motor, rollers, a second motor, and a hydraulic cylinder, the placement plate can rotate using the first motor and rollers, and the tilt angle of the catapult plate can be changed in conjunction with the second motor and hydraulic cylinder, thereby achieving the effect of automatically adjusting the placement direction and tilt angle, thus achieving the purpose of convenient adjustment and avoiding the process of moving the launcher during adjustment, thereby improving the launch rate.

[0004] However, the ejection device in the above structure is generally reset manually, which is very laborious and increases the user's workload. Summary of the Invention

[0005] The purpose of this invention is to provide a multifunctional fixed-wing UAV catapult, which solves the technical problem that the catapult device in the above-mentioned structure in the prior art is generally reset manually, which is very laborious and increases the labor intensity of the user.

[0006] To achieve the above objectives, the present invention provides a multifunctional fixed-wing UAV catapult, comprising a catapult box, a catapult plate, and an auxiliary mechanism. The catapult box contains a crossbar and a catapult block. A first spring is fitted onto the crossbar. The catapult block has a locking groove on its upper surface and a buffer pad on its front end. Supporting blocks are provided on both sides of the catapult block. The catapult box has through holes on both sides. The catapult block and the buffer pad are both fitted onto the crossbar. The first spring supports the catapult block, and the supporting blocks pass through the through holes. The auxiliary mechanism includes a locking element, two transmission elements, a belt body, and a motor. The transmission elements include a push plate and a first screw. The push plate contains... The first threaded groove, a pulley is provided at one end of the first screw, two support blocks are provided on both sides of the ejection box, a limit rod is provided between the two support blocks, the locking member is provided on the ejection box, the push plate is threadedly connected to the first screw and sleeved on the first screw, and also sleeved on the limit rod, the first screw is rotatably connected to the corresponding support block and located between the two support blocks, and the first screw is also provided at the output end of the motor, the belt body is drivenly connected to the corresponding pulley and covers the two pulleys, the motor is fixedly connected to the corresponding support block and located on the support block.

[0007] The locking component includes a second spring and a rocker arm. The ejection box has a through hole at its top. The ejection box is provided with two support plates and a vertical rod. A locking block is hinged to one end of the rocker arm. The locking block has an inclined surface. The second spring is disposed between the rocker arm and the ejection box and is sleeved on the vertical rod. The rocker arm is rotatably connected to the corresponding support plate and is located between the two support plates. The locking block is slidably connected to the ejection box and is located in the through hole.

[0008] The belt body has multiple teeth on its inner side and multiple slots on its outer side, with the teeth and slots being compatible with each other.

[0009] The multi-functional fixed-wing UAV catapult also includes an angle adjustment mechanism and a rotation mechanism. The angle adjustment mechanism is located below the catapult plate, and the rotation mechanism is located below the angle adjustment mechanism.

[0010] The angle adjustment mechanism includes a vertical block, a convex block, and a placement plate. The lower end face of the launch plate has a groove, and both inner sides of the groove have sliding grooves. A round rod is disposed above the vertical block, and an electric telescopic rod is disposed above the convex block. The convex block has a second threaded groove. The upper end face of the placement plate has a convex groove, and a second screw is disposed in the convex groove. One end of the second screw is provided with a first gear. The vertical block is fixedly connected to the electric telescopic rod and is located at the output end of the electric telescopic rod. The round rod is located in the sliding groove, and the vertical block is located in the groove. The convex block is slidably connected to the placement plate and is located in the convex groove. The convex block is sleeved on the second screw. The placement plate is hinged to the launch plate and is located below the launch plate. The rotating mechanism is disposed below the placement plate.

[0011] The angle adjustment mechanism further includes a second gear and a support frame. The second gear is rotatably connected to the support frame and is located inside the support frame. The support frame is fixedly connected to the placement plate and is located at one end of the placement plate. The first gear meshes with the second gear and is located below the second gear.

[0012] The rotating mechanism includes two arc-shaped pieces, a support column, and a base plate. A bearing is mounted on the support column. The end face of the base plate has an annular groove and a circular groove. A limiting groove is located in the circular groove. The two arc-shaped pieces are fixedly connected to the placement plate and are located on the lower end face of the placement plate. The two arc-shaped pieces are also slidably connected to the base plate and are located in the annular groove. The support column is rotatably connected to the base plate and is located in the circular groove. The bearing is located in the limiting groove. The support column is also fixedly connected to the placement plate and is located below the placement plate.

[0013] This invention discloses a multifunctional fixed-wing UAV catapult, comprising a catapult box, a catapult plate, and an auxiliary mechanism. The catapult box contains a crossbar and a catapult block. A first spring is fitted onto the crossbar. The catapult block has a locking groove on its upper surface, a buffer pad on its front end face, and abutment blocks on both sides of the catapult block. The catapult box has through holes on both sides. The catapult block and the buffer pad are both fitted onto the crossbar. The first spring abuts against the catapult block, and the abutment blocks pass through the through holes. The auxiliary mechanism includes a locking component, two transmission components, a belt body, and a motor. The transmission components include a push plate and a first screw. The device comprises a pusher plate with a first threaded groove, a pulley at one end of the first screw, and two support blocks on both sides of the ejection box. A limit rod is positioned between the two support blocks. One of the first screws is driven by a motor, which in turn drives the other first screw via a belt. This causes the two pushers to push the two abutment blocks, moving the ejection block towards the first spring, compressing the spring, and securing it with a locking element. Finally, the spring is released through the locking element, effectively reducing the user's workload. This addresses the problems mentioned in the background section. Attached Figure Description

[0014] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used in conjunction with embodiments of the invention to explain the invention and do not constitute a limitation thereof. In the drawings:

[0015] Figure 1 This is a front view of the first embodiment of the present invention.

[0016] Figure 2 This is the invention Figure 1 A cross-sectional view along line AA in the middle.

[0017] Figure 3 This is the invention Figure 2 A magnified view of a section at point B.

[0018] Figure 4 This is the invention Figure 1 A cross-sectional view of the CC line.

[0019] Figure 5 This is the invention Figure 4 A magnified view of a section at point D.

[0020] Figure 6 This is the invention Figure 4 A cross-sectional view of the EE line.

[0021] Figure 7 This is a front view of the second embodiment of the present invention.

[0022] Figure 8 This is the invention Figure 7 A cross-sectional view of the FF line.

[0023] Figure 9 This is a three-dimensional perspective view of the third embodiment of the present invention.

[0024] 101-Ejection box, 102-Ejection plate, 103-Horizontal bar, 104-Ejection block, 105-First spring, 106-Locking groove, 107-Buffer pad, 108-Supporting block, 109-Through hole, 110-Belt body, 111-Motor, 112-Push plate, 113-First screw, 114-First threaded groove, 115-Pulley, 116-Support block, 117-Limiting rod, 118-Second spring, 119-Pry bar, 120-Through hole, 121-Support piece, 122-Vertical bar, 123-Locking block, 124-Inclined surface, 125-Clamping tooth, 126-Clamping groove, 2 01-Standing block, 202-Convex block, 203-Placement plate, 204-Groove, 205-Slide groove, 206-Round rod, 207-Electric telescopic rod, 208-Second threaded groove, 209-Convex groove, 210-Second screw, 211-First gear, 212-Second gear, 213-Support frame, 214-Arc-shaped piece, 215-Support column, 216-Base plate, 217-Bearing, 218-Annular groove, 219-Round groove, 220-Limiting groove, 301-Universal wheel, 302-Reinforcing rod, 303-Disc, 304-Hydraulic cylinder, 305-Anti-slip mat, 306-Support leg. Detailed Implementation

[0025] The embodiments of the present invention are described in detail below. Examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, but should not be construed as limiting the present invention.

[0026] First embodiment:

[0027] Please see Figures 1-6 The present invention provides a multifunctional fixed-wing UAV catapult, including a catapult box 101, a catapult plate 102 and an auxiliary mechanism. The auxiliary mechanism includes a locking component, two transmission components, a belt body 110 and a motor 111. The transmission components include a push plate 112 and a first screw 113. The locking component includes a second spring 118 and a rocker arm 119.

[0028] In this specific embodiment, the ejection box 101 is provided with a crossbar 103 and an ejection block 104. A first spring 105 is sleeved on the crossbar 103. The ejection block 104 has a locking groove 106 on its upper part. A buffer pad 107 is provided on the front end face of the ejection block 104. Abutment blocks 108 are provided on both sides of the ejection block 104. The ejection box 101 has through holes 109 on both sides. The ejection block 104 and the buffer pad 107 are both sleeved on the crossbar 103. The first spring 105 abuts against the ejection block 104. The abutment block 108 passes through the through hole 109. The ejection plate 102 facilitates the placement of the fixed-wing UAV, thereby compressing the first spring 105, and thus ejecting the fixed-wing UAV by the ejection block 104 and the buffer pad 107.

[0029] The push plate 112 has a first threaded groove 114. A pulley 115 is provided at one end of the first screw 113. Two support blocks 116 are provided on both sides of the ejection box 101. A limit rod 117 is provided between the two support blocks 116. A locking member is provided on the ejection box 101. The push plate 112 is threadedly connected to the first screw 113 and sleeved on the first screw 113, and also sleeved on the limit rod 117. The first screw 113 is rotatably connected to the corresponding support block 116 and located between the two support blocks 116. The first screw 113 is also provided at the output end of the motor 111. The belt body 110 is connected to the... The corresponding pulley 115 is connected to the drive and covers the two pulleys 115. The motor 111 is fixedly connected to the corresponding support block 116 and is located on the support block 116. The motor 111 drives one of the first screws 113, and then the belt body 110 drives the other first screw 113, so that the two push plates 112 push the two abutment blocks 108, thereby moving the ejector block 104 toward the first spring 105, compressing the first spring 105, and fixing it with the locking member. Finally, it is released by the locking member, thereby effectively reducing the labor intensity of the user.

[0030] Secondly, the ejection box 101 has a through hole 120 at its top. Two support plates 121 and a vertical rod 122 are provided on the ejection box 101. A locking block 123 is hinged to one end of the rocker arm 119. The locking block 123 has an inclined surface 124. The second spring 118 is disposed between the rocker arm 119 and the ejection box 101, and is sleeved on the vertical rod 122. The rocker arm 119 is rotatably connected to the corresponding support plate 121 and is located between the two support plates 121. The locking block 123 is slidably connected to the ejection box 101 and is located within the through hole 120. The second spring 118 facilitates the upward lifting of the other end of the rocker arm 119, while one end of the rocker arm 119 moves downward, thereby driving the locking block 123 to insert into the through hole 120. At the same time, when the ejection block 104 moves toward the first spring 105, the locking block 123 can be smoothly inserted into the locking groove 106. Finally, by pressing down the rocker arm 119, one end of the rocker arm 119 is lifted upward, thereby releasing the fixation of the ejection block 104. The ejection block 104 is ejected by the action of the first spring 105 to launch the fixed-wing UAV.

[0031] Meanwhile, the inner side of the belt body 110 is provided with a plurality of teeth 125, and the outer side of the pulley 115 is provided with a plurality of grooves 126, and the teeth 125 and the grooves 126 are adapted to each other. The arrangement of the teeth 125 and the grooves 126 can facilitate ensuring that the rotation speed of the two first screws 113 is consistent.

[0032] When using the multi-functional fixed-wing UAV catapult of this embodiment, by activating the motor 111, one of the first screws 113 is driven to rotate, while the other first screw 113 rotates synchronously under the action of the belt body 110. The two push plates 112, under the action of the first threaded groove 114, push the corresponding abutment block 108 to move. The catapult block 104 then moves towards the first spring 105, compressing the first spring 105. When the locking groove 106 encounters the locking block 123, the catapult... The inclined surface 124 facilitates the locking block 123's entry into the locking groove 106 for fixation. The fixed-wing UAV is then placed on the ejection plate 102, near one end of the ejection box 101. Finally, the rocker arm 119 is pressed down, causing the locking block 123 to be pulled out of the locking groove 106. Under the action of the first spring 105, the ejection block 104 instantly ejects the fixed UAV. This effectively solves the technical problem that the ejection device in the above structure is generally reset manually, which is very laborious and increases the user's workload.

[0033] Second embodiment:

[0034] Based on the first embodiment, the present invention provides a multi-functional fixed-wing UAV catapult, which further includes an angle adjustment mechanism and a rotation mechanism. The angle adjustment mechanism includes a vertical block 201, a convex block 202, a placement plate 203, a second gear 212 and a support frame 213. The rotation mechanism includes two arc-shaped plates 214, a support column 215 and a base plate 216.

[0035] In this specific embodiment, the angle adjustment mechanism is located below the catapult plate 102, and the rotation mechanism is located below the angle adjustment mechanism.

[0036] The lower end face of the ejection plate 102 has a groove 204, and both inner sides of the groove 204 have sliding grooves 205. A round rod 206 is arranged above the upright block 201, and an electric telescopic rod 207 is arranged above the convex block 202. The convex block 202 has a second threaded groove 208. The upper end face of the placement plate 203 has a convex groove 209, and a second screw 210 is arranged in the convex groove 209. One end of the second screw 210 is provided with a first gear 211. The upright block 201 is fixedly connected to the electric telescopic rod 207 and is located at the output end of the electric telescopic rod 207. The round rod 206 is located in the sliding groove 205, and the upright block 201 is located in the groove 204. The convex block 202 is slidably connected to the placement plate 203 and located within the convex groove 209. The convex block 202 is sleeved on the second screw 210. The placement plate 203 is hinged to the catapult plate 102 and located below the catapult plate 102. The rotating mechanism is located below the placement plate 203. Through the rotation of the first gear 211, the second screw 210 rotates. The convex block 202 moves under the action of the second threaded groove 208, thereby driving the electric telescopic rod 207 to move. Then, the electric telescopic rod 207 is activated, causing it to move upward. At this time, the tilt angle of the catapult plate 102 can be adjusted, thereby improving practicality.

[0037] Secondly, the second gear 212 is rotatably connected to the support frame 213 and is located inside the support frame 213. The support frame 213 is fixedly connected to the placement plate 203 and is located at one end of the placement plate 203. The first gear 211 is meshed with the second gear 212 and is located below the second gear 212. It should be noted that the volume of the first gear 211 is many times that of the second gear 212. According to the lever principle, the transmission between the second gear 212 and the first gear 211 can save effort.

[0038] Meanwhile, a bearing 217 is provided on the support column 215, and the end face of the base plate 216 has an annular groove 218 and a circular groove 219. A limiting groove 220 is provided in the circular groove 219. Two arc-shaped pieces 214 are fixedly connected to the placement plate 203 and located on the lower end face of the placement plate 203. The two arc-shaped pieces 214 are also slidably connected to the base plate 216 and located in the annular groove 218. The support column 215 is rotatably connected to the base plate 216 and located in the circular groove 219. The bearing 217 is located in the limiting groove 220. The support column 215 is also fixedly connected to the placement plate 203 and located below the placement plate 203. By rotating the placement plate 203, the rotation of the placement plate 203 can be restricted under the action of the support column 215 and the bearing 217, so that the ejection plate 102 can be ejected in any direction.

[0039] When using the multi-functional fixed-wing UAV catapult of this embodiment, the rotation of the first gear 211 causes the second screw 210 to rotate, and the convex block 202 moves under the action of the second threaded groove 208, thereby driving the electric telescopic rod 207 to move. Then, activating the electric telescopic rod 207 causes it to move upwards. At this time, the tilt angle of the catapult plate 102 can be adjusted, thus improving practicality. It should be noted that the volume of the first gear 211 is many times that of the second gear 212. According to the lever principle, the transmission between the second gear 212 and the first gear 211 can save effort.

[0040] Third embodiment:

[0041] The multi-functional fixed-wing UAV catapult also includes a moving mechanism and multiple support members. The moving mechanism is fixedly connected to the base plate 216 and located below the base plate 216. The multiple support members are respectively fixedly connected to the base plate 216 and located below the base plate 216, and the moving mechanism is located between the multiple support members.

[0042] The moving mechanism includes multiple casters 301, multiple reinforcing rods 302, a disc 303, and a hydraulic cylinder 304. The multiple casters 301 are fixedly connected to the disc 303 and located below the disc 303. The multiple reinforcing rods 302 are fixedly connected to the base plate 216 and located below the base plate 216. The multiple reinforcing rods 302 are also slidably connected to the disc 303 and pass through the disc 303. The disc 303 is fixedly connected to the hydraulic cylinder 304 and located at the output end of the hydraulic cylinder 304. The hydraulic cylinder 304 is fixedly connected to the base plate 216 and located below the base plate 216.

[0043] The support includes an anti-slip pad 305 and a support leg 306. The anti-slip pad 305 is fixedly connected to the support leg 306 and is located below the support leg 306. The support leg 306 is fixedly connected to the base plate 216 and is located below the base plate 216.

[0044] Based on the second embodiment, please refer to Figure 9 ,in Figure 9 This is a three-dimensional perspective view of the third embodiment of the present invention.

[0045] The present invention provides a multifunctional fixed-wing UAV catapult, which also includes a moving mechanism and multiple supporting components. The moving mechanism includes multiple casters 301, multiple reinforcing rods 302, a disc 303 and a hydraulic cylinder 304. The supporting components include anti-slip pads 305 and supporting legs 306.

[0046] In this specific embodiment, the moving mechanism is fixedly connected to the base plate 216 and located below the base plate 216. The plurality of supporting members are respectively fixedly connected to the base plate 216 and located below the base plate 216, and the moving mechanism is located between the plurality of supporting members.

[0047] In this configuration, multiple casters 301 are fixedly connected to the disc 303 and located below the disc 303. Multiple reinforcing rods 302 are fixedly connected to the base plate 216 and located below the base plate 216. The reinforcing rods 302 are also slidably connected to the disc 303 and pass through the disc 303. The disc 303 is fixedly connected to the hydraulic cylinder 304 and located at the output end of the hydraulic cylinder 304. The hydraulic cylinder 304 is fixedly connected to the base plate 216 and located below the base plate 216. By activating the hydraulic cylinder 304, the disc 303 is moved towards the ground, causing the casters 301 to contact the ground. This allows the casters 301 to replace the supporting members in supporting the base plate 216, facilitating movement.

[0048] Secondly, the anti-slip mat 305 is fixedly connected to the support leg 306 and located below the support leg 306. The support leg 306 is fixedly connected to the base plate 216 and located below the base plate 216. The anti-slip mat 305 can improve the grip and thus prevent slipping.

[0049] When using the multi-functional fixed-wing UAV catapult of this embodiment, by activating the hydraulic cylinder 304, the hydraulic cylinder 304 pushes the disc 303 towards the ground, thereby causing the caster wheel 301 to contact the ground, and thus the caster wheel 301 replaces the support member to support the base plate 216, thereby facilitating movement. The anti-slip pad 305 can improve the grip, thereby avoiding slippage.

[0050] The above-disclosed embodiments are merely one or more preferred embodiments of this application and should not be construed as limiting the scope of this application. Those skilled in the art can understand that all or part of the processes for implementing the above embodiments and equivalent changes made in accordance with the claims of this application still fall within the scope of this application.

Claims

1. A multi-functional fixed-wing UAV catapult, comprising a catapult box and a catapult plate, wherein a crossbar and a catapult block are disposed inside the catapult box, a first spring is sleeved on the crossbar, a locking groove is provided above the catapult block, a buffer pad is provided on the front end face of the catapult block, and abutment blocks are provided on both sides of the catapult block. The catapult box has through holes on both sides, the catapult block and the buffer pad are both sleeved on the crossbar, the first spring abuts against the catapult block, and the abutment blocks penetrate the through holes, characterized in that... It also includes auxiliary mechanisms; The auxiliary mechanism includes a locking component, two transmission components, a belt body, and a motor. Each transmission component includes a push plate and a first screw. The push plate has a first threaded groove. One end of the first screw is equipped with a pulley. Two support blocks are provided on both sides of the ejection box, and a limit rod is provided between the two support blocks. The locking component is mounted on the ejection box. The push plate is threadedly connected to the first screw and sleeved on the first screw, and also sleeved on the limit rod. The first screw is rotatably connected to the corresponding support block and located between the two support blocks. The first screw is also located at the output end of the motor. The belt body is drively connected to the corresponding pulley and covers the area between the two pulleys. The motor is fixedly connected to the corresponding support block and located on the support block.

2. The multi-functional fixed-wing UAV catapult as described in claim 1, characterized in that, The locking component includes a second spring and a rocker arm. The ejection box has a through hole at its top. The ejection box is provided with two support plates and a vertical rod. A locking block is hinged to one end of the rocker arm. The locking block has an inclined surface. The second spring is disposed between the rocker arm and the ejection box and is sleeved on the vertical rod. The rocker arm is rotatably connected to the corresponding support plate and is located between the two support plates. The locking block is slidably connected to the ejection box and is located in the through hole.

3. The multi-functional fixed-wing UAV catapult as described in claim 2, characterized in that, The inner side of the belt body is provided with multiple teeth, and the outer side of the pulley is provided with multiple slots, and the teeth are adapted to the slots.

4. The multi-functional fixed-wing UAV catapult as described in claim 3, characterized in that, The multi-functional fixed-wing UAV catapult also includes an angle adjustment mechanism and a rotation mechanism. The angle adjustment mechanism is located below the catapult plate, and the rotation mechanism is located below the angle adjustment mechanism.

5. The multi-functional fixed-wing UAV catapult as described in claim 4, characterized in that, The angle adjustment mechanism includes a vertical block, a convex block, and a placement plate. The lower end face of the launch plate has a groove, and both inner sides of the groove have sliding grooves. A round rod is disposed above the vertical block, and an electric telescopic rod is disposed above the convex block. The convex block has a second threaded groove. The upper end face of the placement plate has a convex groove, and a second screw is disposed in the convex groove. One end of the second screw is provided with a first gear. The vertical block is fixedly connected to the electric telescopic rod and is located at the output end of the electric telescopic rod. The round rod is located in the sliding groove, and the vertical block is located in the groove. The convex block is slidably connected to the placement plate and is located in the convex groove. The convex block is sleeved on the second screw. The placement plate is hinged to the launch plate and is located below the launch plate. The rotating mechanism is disposed below the placement plate.

6. The multi-functional fixed-wing UAV catapult as described in claim 5, characterized in that, The angle adjustment mechanism further includes a second gear and a support frame. The second gear is rotatably connected to the support frame and is located inside the support frame. The support frame is fixedly connected to the placement plate and is located at one end of the placement plate. The first gear is meshed with the second gear and is located below the second gear.

7. The multi-functional fixed-wing UAV catapult as described in claim 6, characterized in that, The rotating mechanism includes two arc-shaped plates, a support column, and a base plate. A bearing is provided on the support column. The end face of the base plate has an annular groove and a circular groove. A limiting groove is provided in the circular groove. The two arc-shaped plates are fixedly connected to the placement plate and are located on the lower end face of the placement plate. The two arc-shaped plates are also slidably connected to the base plate and are located in the annular groove. The support column is rotatably connected to the base plate and is located in the circular groove. The bearing is located in the limiting groove. The support column is also fixedly connected to the placement plate and is located below the placement plate.

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