An unmanned aerial vehicle landing gear for geographic information mapping

Abstract

The application discloses a kind of unmanned plane landing gear for geographic information mapping, including mounting plate and fixedly installed in the bracket rod below both sides of mounting plate, the mounting hole is formed in the mounting plate;The bottom of the bracket rod is fixedly installed with a rectangular shell;The bottom opening of the rectangular shell is embedded with a shape taking mechanism, and the upper part of the inside of the rectangular shell is provided with a buffer assembly.The beneficial effects of the application are that by setting the shape taking mechanism at the bottom, during the landing process, the shape taking mechanism is in contact with the ground, automatically adapts to and adapts to different ground conditions, meets the landing under the condition of uneven outdoor ground when outdoor geographic information collection is shot, ensures the stability of landing;After suitable ground, buffer through buffer assembly, to avoid landing impact.

Description

A landing gear for unmanned aerial vehicles (UAVs) used for geographic information mapping Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) landing gear, and in particular to a UAV landing gear for geographic information mapping. Background Technology

[0002] Geographic information mapping refers to a discipline that uses a series of technical means to collect, process, manage, store, transmit, maintain, update, and use information about the Earth's surface in terms of spatial location, morphology, structure, natural and human elements. Its mapping often uses drones for high-altitude photography to achieve information collection.

[0003] Since geographic information surveying and mapping is often carried out outdoors, the ground is uneven. In some mountainous, plateau, and hilly areas, the ground is often quite pitted. During the descent of a drone, it may be difficult to find a flat surface. As a result, the drone may need to land on pitted ground. Currently, the drone landing gear lacks an adaptive adjustment design and cannot be adapted to different pitted surfaces. When landing on pitted ground, its descent stability is not guaranteed, and it may tip over or even be damaged.

[0004] However, most drone designs are geared towards taking off on flat surfaces, and there are no drones specifically designed for geographic information mapping yet. Therefore, how to ensure smooth landing of drones on uneven surfaces remains a blank slate. Summary of the Invention

[0005] To address the technical challenge of ensuring a smooth landing for drones on uneven surfaces, this invention designs a drone landing gear for geographic information mapping. By incorporating a shape-taking mechanism, the ground topography is acquired, allowing the drone to adapt to varying ground conditions and achieve a smooth landing on uneven surfaces. Furthermore, the design provides cushioning on uneven surfaces to prevent landing impact.

[0006] The objective of this invention is achieved as follows:

[0007] A UAV landing gear for geographic information mapping includes a mounting plate and frame poles fixedly mounted on both sides below the mounting plate. The mounting plate has mounting holes. A rectangular shell is fixedly mounted on the bottom of each frame pole. A shaping mechanism is embedded in the bottom opening of the rectangular shell, and a buffer component is provided on the upper part of the interior of the rectangular shell.

[0008] Furthermore, the shaping mechanism is composed of several thin rods arranged in a rectangular array, and the thin rods are filled at the bottom of the rectangular shell; there is a gap of 0.4-0.6mm between two adjacent thin rods.

[0009] Furthermore, a locking assembly is provided between two adjacent thin rods. The locking assembly is fixedly installed in the middle of one of the thin rods, and a long groove is formed on the outer wall of the other thin rod along the length direction. The locking assembly extends into the long groove.

[0010] Furthermore, the locking assembly includes a block and a miniature air pump installed inside the block; the block has a chamber inside, with both ends of the chamber communicating with the outside of the block, and two piston rods symmetrically arranged inside the chamber. Each piston rod is formed by a pressure column and a piston disc, with the end of the pressure column away from the piston disc extending into the end of the chamber, forming a gas chamber between the two piston discs. The output end of the miniature air pump is connected to an air pipe, the end of which communicates with the gas chamber. A miniature solenoid valve is fixedly installed on the block, with one end of the solenoid valve located inside the gas chamber and the other end communicating with the outside of the block; a one-way valve is provided at the connection between the miniature air pump and the air pipe; and a miniature air pressure sensor is provided inside the gas chamber.

[0011] Furthermore, a reset spring is provided inside the chamber, and the reset spring is sleeved on the pressure column, which is elastically connected to the block through the reset spring.

[0012] Furthermore, the locking assembly includes a protective shell and a servo motor fixedly installed inside the thin rod wall. A worm gear and a rotating shaft are rotatably installed inside the protective shell. A worm wheel is fixedly sleeved on the rotating shaft. The worm gear meshes with the worm wheel. One end of the worm gear is fixedly connected to the output shaft end of the servo motor. One end of the rotating shaft is provided with an elastic pressure member.

[0013] Furthermore, the elastic pressure member is composed of a central block, a pressure block, a guide groove, a compression spring, and a guide post. The central part of the central block is fixedly connected to one end of the rotating shaft. Both sides of the central block are elastically connected to pressure blocks through compression springs. The pressure blocks are fixedly connected to guide posts, and the guide posts are connected to the guide grooves opened on the central block with clearance fit.

[0014] Furthermore, a guide hole is provided at the top end of the thin rod, and an inner cavity is provided inside the thin rod. The inner cavity communicates with the guide hole, and a guide rod is connected to the guide hole with clearance fit. The top end of the guide rod is fixedly connected to the top inner wall of the rectangular shell, and an anti-detachment block is fixedly installed at the bottom end of the guide rod, and the anti-detachment block is located in the inner cavity.

[0015] Furthermore, a groove is provided at the bottom of the anti-detachment block, and a displacement sensor is installed in the groove.

[0016] Furthermore, the buffer assembly includes a fixed upper plate and a movable lower plate; the edge of the fixed upper plate is fixedly installed to the upper inner wall of the rectangular shell by fixing screws, and multiple buffer airbags are installed at the bottom of the fixed upper plate. Buffer springs are installed at the bottom of the buffer airbags, and the bottom ends of the buffer springs are connected to the movable lower plate. Several through holes are opened on the surface of the movable lower plate, and the through holes are connected to the guide rod with clearance fit.

[0017] The advantages of this application are as follows: The UAV landing gear proposed in this application for geographic information mapping, by setting a shape-taking mechanism at the bottom, automatically adapts to and accommodates different ground flatness conditions through contact with the ground during landing, meeting the landing requirements of outdoor geographic information collection and shooting in situations where the outdoor ground is uneven and not flat, thus ensuring landing stability; after adapting to the ground, a buffer component is used to cushion the impact of landing. Attached Figure Description

[0018] Figure 1 is a schematic diagram of the overall structure of the UAV landing gear for geographic information mapping according to the present invention;

[0019] Figure 2 is a schematic diagram of the distribution of thin rods at the bottom of a rectangular shell;

[0020] Figure 3 is a schematic diagram of the internal cross-sectional structure of the rectangular shell;

[0021] Figure 4 is an enlarged structural schematic diagram of part A in Figure 3;

[0022] Figure 5 is a schematic diagram showing the position of the locking component on the thin rod;

[0023] Figure 6 is a schematic diagram showing the position of the long groove on the thin rod;

[0024] Figure 7 is a schematic diagram of the internal cross-sectional structure of the thin rod;

[0025] Figure 8 is a schematic diagram of the structure of the conductive pillar and conductive strip;

[0026] Figure 9 is a schematic diagram of the internal structure of the block;

[0027] Figure 10 is a schematic diagram of the installation structure of the elastic pressure component;

[0028] Figure 11 is a schematic diagram of the elastic pressure component.

[0029] In the diagram: 1. Mounting plate; 2. Frame rod; 3. Rectangular shell; 4. Thin rod; 401. Guide hole; 402. Inner cavity; 5. Fixing screw; 6. Movable lower plate; 7. Fixed upper plate; 8. Buffer airbag; 9. Buffer spring; 10. Locking assembly; 11. Long groove; 12. Anti-detachment block; 13. Displacement sensor; 14. Connecting cable; 15. Carrier bar; 16. Conductive post; 17. Conductive strip; 1701. Rubber gasket; 18. Control board; 19. 20. Block; 21. Miniature air pump; 22. Air pipe; 23. Chamber; 24. Pressure column; 25. Piston disc; 26. Return spring; 27. Miniature air pressure sensor; 28. Miniature solenoid valve; 29. ​​Servo motor; 30. Protective shell; 31. Worm gear; 32. Rotating shaft; 33. Worm wheel; 33. Elastic pressure component; 3301. Central block; 3302. Pressure block; 3303. Guide groove; 3304. Compression spring; 3305. Guide column; 34. Guide rod. Detailed Implementation

[0030] The specific embodiments of the present invention will now be described in further detail with reference to the accompanying drawings.

[0031] Example 1

[0032] Please refer to Figures 1-9. A UAV landing gear for geographic information mapping includes a mounting plate 1 and support poles 2 fixedly installed on both sides below the mounting plate 1. The mounting plate 1 has mounting holes. A rectangular shell 3 is fixedly installed at the bottom of each support pole 2. A shape-taking mechanism is embedded in the bottom opening of the rectangular shell 3, and a buffer component is provided on the upper part of the interior of the rectangular shell 3. During the landing process, the UAV contacts the ground through the shape-taking mechanism and automatically adapts to different ground flatness conditions, meeting the landing requirements of outdoor geographic information collection and shooting when the outdoor ground is uneven and lacks flatness.

[0033] In specific implementation, as shown in Figures 2-3, the shaping mechanism consists of several thin rods 4 arranged in a rectangular array, and these thin rods 4 are filled and arranged at the bottom of the rectangular shell 3. There is a gap of 0.4-0.6mm between two adjacent thin rods 4. When the thin rods 4 are in contact with the ground, and the ground is uneven or pitted, the height of the bottom of different thin rods 4 after contacting the ground is adapted to the height of the contact position. The length of the thin rods 4 retracted into the rectangular shell is different at different positions, so as to achieve shaping adaptation. The overall bottom surface formed by the several thin rods 4 is adapted to the flatness of the ground.

[0034] Furthermore, a locking assembly 10 is provided between two adjacent thin rods 4. The locking assembly 10 is fixedly installed to the middle of one of the two adjacent thin rods 4, while the outer wall of the other thin rod 4 has a long groove 11 along the length direction. The locking assembly 10 extends into the long groove 11. When making contact with the ground and taking shape, the ground that the bottom ends of different thin rods 4 need to contact is of different heights and flatness. There may be relative movement between adjacent thin rods 4. When there is relative movement, the locking assembly 10 does not lock, and the locking assembly 10 and the long groove 11 are not locked or pressed together to avoid affecting the relative movement between the thin rods.

[0035] In specific implementation, a guide hole 401 is provided at the top of the thin rod 4, and an inner cavity 402 is provided inside the thin rod 4. The inner cavity 402 communicates with the guide hole 401. A guide rod 34 is connected to the guide hole 401 with clearance fit. The top of the guide rod 34 is fixedly connected to the top inner wall of the rectangular shell 3. An anti-detachment block 12 is fixedly installed at the bottom of the guide rod 34, and the anti-detachment block 12 is located in the inner cavity 402. A groove is provided at the bottom of the anti-detachment block 12, and a displacement sensor 13 is installed in the groove. The vertical movement of the thin rod 4 is guided by the guide hole 401 and the guide rod 34. The displacement sensor 13 is further provided to determine the displacement of each thin rod 4. At the same time, the displacement sensor 13 is electrically connected to the control system of the UAV to provide feedback. When it is determined that all thin rods have moved, the shaping is completed. After the shaping is completed, it is locked by the locking component so that all thin rods 4 form a whole.

[0036] As a specific technical solution, as shown in Figure 9, the locking assembly 10 includes a block 19 and a miniature air pump 20 installed inside the block 19. A chamber 22 is formed inside the block 19, with both ends of the chamber 22 communicating with the outside of the block 19. Two piston rods are symmetrically arranged inside the chamber 22. Each piston rod is formed by a pressure column 23 and a piston disc 24. The end of the pressure column 23 away from the piston disc 24 extends into the end of the chamber 22, forming a gas chamber between the two piston discs 24. The output end of the miniature air pump 20 is connected to an air pipe 21, the end of which communicates with the gas chamber. A miniature solenoid valve 27 is fixedly installed on the block 19, with one end of the solenoid valve 27 located inside the gas chamber and the other end communicating with the outside of the block 19. The connection between the miniature air pump 20 and the air pipe 21... A one-way valve is provided at the location; a miniature air pressure sensor 26 is provided in the gas chamber; a return spring 25 is provided inside the chamber 22, and the return spring 25 is sleeved on the pressure column 23. The pressure column 23 is elastically connected to the block 19 through the return spring 25. As shown in Figure 9, it is not locked at this time. When locking, air is introduced into the air pipe 21 through the miniature air pump 20 and enters the gas chamber between the two piston discs 24 to increase the air pressure. This drives the piston discs 24 and the pressure column 23 to move together, so that the end of the pressure column 23 extends out of the chamber 22 and can press against the groove wall of the long groove 11. The miniature air pressure sensor 26 monitors the sensing air pressure in real time. When the set value is reached, the miniature air pump 20 stops working, maintaining the pressure column 23 at the specified pressure against the groove wall of the long groove 11 to increase the friction. The high friction provides positioning and locking between the thin rods 4.

[0037] During locking, the pressure column 23 moves, compressing the return spring 25 and generating a return force. During unlocking, the micro solenoid valve 27 is opened to release air from the gas chamber, reducing the air pressure. The return spring 25 provides a reset drive, causing the pressure column 23 to reset. The pressure column 23 does not contact the groove wall of the long groove 11 and is not locked.

[0038] As shown in Figure 3, in specific implementation, the buffer assembly includes a fixed upper plate 7 and a movable lower plate 6. The edge of the fixed upper plate 7 is fixedly installed to the upper inner wall of the rectangular shell 3 by fixing screws 5. Multiple buffer airbags 8 are installed at the bottom of the fixed upper plate 7, and buffer springs 9 are installed at the bottom of the buffer airbags 8. The bottom end of the buffer springs 9 is connected to the movable lower plate 6. Several through holes are opened on the surface of the movable lower plate 6, and the through holes are connected to the guide rods 34 with clearance fit. After the shaping mechanism takes shape, all the thin rods 4 form a whole. The UAV continues to land. The whole formed by the shaping mechanism is blocked by the ground and continues to be retracted into the rectangular shell 3, contacting the movable lower plate 6 at the bottom of the buffer assembly. The buffer assembly buffers the impact and reduces the impact. The buffer is provided by the buffer springs 9 and the elasticity of the buffer springs 9 to reduce the impact force of the fall. Furthermore, the movable lower plate 6 is provided with through holes to avoid the guide rods 34, so that the guide rods 34 and the movable lower plate 6 do not affect each other.

[0039] The control system and power supply of the UAV are electrically connected to the control board 18 via a connecting cable 14. The control board 18 is located inside the thin rod 4. Since the thin rod 4 has a structure that can slide up and down and move, the electrical connection between the control board 18 and the connecting cable 14 is achieved using a carrier bar 15, conductive posts 16, and conductive strips 17. The carrier bar 15 is fixedly installed on the anti-detachment block 12. The carrier bar 15 is made of insulating plastic. The conductive posts 16 are fixedly installed on the carrier bar 15. The number of conductive posts 16 is determined by the number of wires in the connecting cable 14 that need to be connected to the control board 18. Each wire needs to be connected to one conductive post 16. The number of conductive strips 17 is the same as the number of conductive posts 16. Each conductive post 16 contacts one conductive post. The conductive strip 17 is fixedly mounted with a rubber gasket 1701, which is adhered to the cavity wall of the inner cavity 402, so that the conductive strip 17 is set along the length of the inner cavity 402. The bottom of the conductive strip 17 is connected to the control board 18. When the thin rod 4 moves up and down, the conductive post 16 slides along the length of the conductive strip 17 to maintain continuous contact, thereby ensuring the electrical connection between the connecting cable 14 and the control board 18 in the moving state. The control board 18 is electrically connected to the micro air pump 20, micro air pressure sensor 26, and micro solenoid valve 27 in the block 19, thereby realizing the electrical control of the micro air pump 20, micro air pressure sensor 26, and micro solenoid valve 27 by the UAV.

[0040] Example 2

[0041] Please refer to Figures 1-8 and 10-11. A UAV landing gear for geographic information mapping includes a mounting plate 1 and support poles 2 fixedly installed on both sides below the mounting plate 1. The mounting plate 1 has mounting holes. A rectangular shell 3 is fixedly installed at the bottom of each support pole 2. A shape-taking mechanism is embedded in the bottom opening of the rectangular shell 3, and a buffer component is provided on the upper part of the interior of the rectangular shell 3. During the landing process, the UAV contacts the ground through the shape-taking mechanism and automatically adapts to different ground flatness conditions, meeting the landing requirements of outdoor geographic information collection and shooting when the outdoor ground is uneven and lacks flatness.

[0042] In specific implementation, as shown in Figures 2-3, the shaping mechanism consists of several thin rods 4 arranged in a rectangular array, and these thin rods 4 are filled and arranged at the bottom of the rectangular shell 3. There is a gap of 0.4-0.6mm between two adjacent thin rods 4. When the thin rods 4 are in contact with the ground, and the ground is uneven or pitted, the height of the bottom of different thin rods 4 after contacting the ground is adapted to the height of the contact position. The length of the thin rods 4 retracted into the rectangular shell is different at different positions, so as to achieve shaping adaptation. The overall bottom surface formed by the several thin rods 4 is adapted to the flatness of the ground.

[0043] Furthermore, a locking assembly 10 is provided between two adjacent thin rods 4. The locking assembly 10 is fixedly installed to the middle of one of the two adjacent thin rods 4, while the outer wall of the other thin rod 4 has a long groove 11 along the length direction. The locking assembly 10 extends into the long groove 11. When making contact with the ground and taking shape, the ground that the bottom ends of different thin rods 4 need to contact is of different heights and flatness. There may be relative movement between adjacent thin rods 4. When there is relative movement, the locking assembly 10 does not lock, and the locking assembly 10 and the long groove 11 are not locked or pressed together to avoid affecting the relative movement between the thin rods.

[0044] In specific implementation, a guide hole 401 is provided at the top of the thin rod 4, and an inner cavity 402 is provided inside the thin rod 4. The inner cavity 402 communicates with the guide hole 401. A guide rod 34 is connected to the guide hole 401 with clearance fit. The top of the guide rod 34 is fixedly connected to the top inner wall of the rectangular shell 3. An anti-detachment block 12 is fixedly installed at the bottom of the guide rod 34, and the anti-detachment block 12 is located in the inner cavity 402. A groove is provided at the bottom of the anti-detachment block 12, and a displacement sensor 13 is installed in the groove. The vertical movement of the thin rod 4 is guided by the guide hole 401 and the guide rod 34. The displacement sensor 13 is further provided to determine the displacement of each thin rod 4. At the same time, the displacement sensor 13 is electrically connected to the control system of the UAV to provide feedback. When it is determined that all thin rods have moved, the shaping is completed. After the shaping is completed, it is locked by the locking component so that all thin rods 4 form a whole.

[0045] As a specific technical solution, as shown in Figures 10-11, the locking assembly 10 includes a protective shell 29 and a servo motor 28 fixedly installed inside the wall of the thin rod 4. A worm gear 30 and a rotating shaft 31 are rotatably installed inside the protective shell 29. A worm wheel 32 is fixedly sleeved on the rotating shaft 31. The worm gear 30 and the worm wheel 32 are meshed together. One end of the worm gear 30 is fixedly connected to the output shaft end of the servo motor 28. One end of the rotating shaft 31 is provided with an elastic compression... Component 33; The elastic pressing component 33 is composed of a central block 3301, a pressing block 3302, a guide groove 3303, a compression spring 3304, and a guide post 3305. The central part of the central block 3301 is fixedly connected to one end of the rotating shaft 31. Both sides of the central block 3301 are elastically connected to the pressing block 3302 through the compression spring 3304. The pressing block 3302 is fixedly connected to the guide post 3305. The guide post 3305 is connected to the guide post 3305 on the central block 3301. The guide groove 3303 is connected with a clearance fit; as shown in Figure 10-11, the locking assembly 10 is in an unlocked state at this time. During the locking process, the servo motor 28 drives the worm gear 30 to rotate. Through the meshing transmission between the worm gear 30 and the worm wheel 32, the rotating shaft 31 and the elastic pressure member 33 can be driven to rotate together. Specifically, it needs to rotate 90 degrees. In the uncompressed state, the length of the elastic pressure member 33 is greater than the width of the long groove 11. During the 90-degree rotation, the long groove 11 compresses the elastic pressure member 33, so that the pressure block 3302 is close to the middle block 3301. The guide groove 3303 and the guide post 3305 guide the movement between the pressure block 3302 and the middle block 3301. At the same time, the compression spring 2204 is compressed. After rotating 90 degrees, the compression spring 2204 is fully compressed, providing pressure to the pressure block 3302, so that the pressure block 3302 presses against the groove wall of the long groove 11, increasing the friction. Through the high friction, locking and positioning are provided.

[0046] During unlocking, the servo motor 28 drives the elastic pressure piece 33 to rotate 90 degrees in the opposite direction to reset it. The pressure block 3302 does not contact the long groove 11, thus canceling the positioning and locking.

[0047] The transmission is achieved by using a worm gear 30 and a worm wheel 32. The worm gear 30 and worm wheel 32 provide self-locking, and the worm wheel 32 cannot drive the worm gear 30 to rotate, thus maintaining the angle of the elastic pressure member 33 after angle adjustment.

[0048] As shown in Figure 3, in specific implementation, the buffer assembly includes a fixed upper plate 7 and a movable lower plate 6. The edge of the fixed upper plate 7 is fixedly installed to the upper inner wall of the rectangular shell 3 by fixing screws 5. Multiple buffer airbags 8 are installed at the bottom of the fixed upper plate 7, and buffer springs 9 are installed at the bottom of the buffer airbags 8. The bottom end of the buffer springs 9 is connected to the movable lower plate 6. Several through holes are opened on the surface of the movable lower plate 6, and the through holes are connected to the guide rods 34 with clearance fit. After the shaping mechanism takes shape, all the thin rods 4 form a whole. The UAV continues to land. The whole formed by the shaping mechanism is blocked by the ground and continues to be retracted into the rectangular shell 3, contacting the movable lower plate 6 at the bottom of the buffer assembly. The buffer assembly buffers the impact and reduces the impact. The buffer is provided by the buffer springs 9 and the elasticity of the buffer springs 9 to reduce the impact force of the fall. Furthermore, the movable lower plate 6 is provided with through holes to avoid the guide rods 34, so that the guide rods 34 and the movable lower plate 6 do not affect each other.

[0049] The control system and power supply of the UAV are electrically connected to the control board 18 via connecting cable 14. The control board 18 is located inside the thin rod 4. Since the thin rod 4 has a structure that can slide up and down and move, the electrical connection between the control board 18 and the connecting cable 14 is achieved using a carrier bar 15, conductive posts 16, and conductive strips 17. The carrier bar 15 is fixedly installed on the anti-detachment block 12. The carrier bar 15 is made of insulating plastic. The conductive posts 16 are fixedly installed on the carrier bar 15. The number of conductive posts 16 is determined by the number of wires in the connecting cable 14 that need to be connected to the control board 18. Each wire needs to be connected to one conductive post 16. The number of conductive strips 17 is related to the number of conductive posts 17. The number of posts 16 is the same, and each conductive post 16 contacts a conductive strip 17. The conductive strip 17 is fixedly mounted with a rubber gasket 1701, which is adhered to the cavity wall of the inner cavity 402, so that the conductive strip 17 is set along the length of the inner cavity 402. The bottom of the conductive strip 17 is connected to the control board 18. When the thin rod 4 moves up and down, the conductive post 16 slides along the length of the conductive strip 17, maintaining continuous contact, thereby ensuring the electrical connection between the connecting cable 14 and the control board 18 in the moving state. The control board 18 is electrically connected to the servo motor 28, thereby realizing the UAV's electrical control of the servo motor 28.

[0050] The control board 18 is a circuit board with connection circuits and a controller, which can be a single-chip microcomputer controller.

[0051] After landing, the drone takes off again, unlocking the shaping mechanism and releasing the lock between adjacent thin rods 4. The thin rods 4 then fall and reset under their own weight. After resetting, the internal state of the thin rods 4 is shown in Figure 7.

[0052] The circuits, electronic components, and modules involved are all existing technologies, which can be fully implemented by those skilled in the art, and need not be elaborated upon. The content protected by this application does not involve any improvement to the software and methods.

[0053] The above description is merely a preferred embodiment of this application and is not intended to limit the application. For those skilled in the art,

[0054] This application may be subject to various modifications and variations. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application shall be included within the scope of protection of this application.

Claims

1. A landing gear for a UAV used for geographic information mapping, comprising a mounting plate (1) and frame rods (2) fixedly mounted on both sides below the mounting plate (1), wherein the mounting plate (1) has mounting holes; characterized in that: A rectangular shell (3) is fixedly installed at the bottom of each of the support rods (2); a shaping mechanism is embedded in the bottom opening of the rectangular shell (3), and a buffer assembly is provided above the interior of the rectangular shell (3); the shaping mechanism is composed of several thin rods (4) arranged in a rectangular array, and several thin rods (4) are filled at the bottom of the rectangular shell (3); there is a gap of 0.4-0.6mm between two adjacent thin rods (4); a locking assembly (10) is provided between two adjacent thin rods (4), the locking assembly (10) is fixedly installed in the middle of one thin rod (4), and a long groove (11) is opened along the length direction on the outer wall of the other thin rod (4), and the locking assembly (10) extends into the long groove (11); a guide hole (401) is opened at the top of the thin rod (4), and an inner cavity (402) is provided inside the thin rod (4), the inner cavity (402) and the guide hole (401) are connected. 1) Connected, the guide hole (401) is connected to the guide rod (34) with clearance fit. The top of the guide rod (34) is fixedly connected to the top inner wall of the rectangular shell (3). The bottom of the guide rod (34) is fixedly installed with an anti-detachment block (12), and the anti-detachment block (12) is located in the inner cavity (402). The bottom of the anti-detachment block (12) is provided with a groove, and a displacement sensor (13) is installed in the groove. The buffer assembly includes a fixed upper plate (7) and a movable lower plate (6). The edge of the fixed upper plate (7) is fixedly installed to the upper inner wall of the rectangular shell (3) by a fixing screw (5). Multiple buffer airbags (8) are installed at the bottom of the fixed upper plate (7). Buffer springs (9) are installed at the bottom of the buffer airbags (8). The bottom of the buffer springs (9) is connected to the movable lower plate (6). Several through holes are opened on the surface of the movable lower plate (6). The through holes are connected to the guide rod (34) with clearance fit.

2. The UAV landing gear for geographic information mapping according to claim 1, characterized in that: The locking assembly (10) includes a block (19) and a miniature air pump (20) installed inside the block (19). The block (19) has a chamber (22) inside, with both ends of the chamber (22) communicating with the outside of the block (19). Two piston rods are symmetrically arranged inside the chamber (22). Each piston rod is fixedly connected by a pressure column (23) and a piston disc (24). The end of the pressure column (23) away from the piston disc (24) extends into the end of the chamber (22). The two piston discs (24)... A gas chamber is formed between the two parts. The output end of the micro air pump (20) is connected to an air pipe (21). The end of the air pipe (21) is connected to the gas chamber. A micro solenoid valve (27) is fixedly installed on the block (19). One end of the micro solenoid valve (27) is located inside the gas chamber, and the other end of the micro solenoid valve (27) is connected to the outside of the block (19). A one-way valve is provided at the connection between the micro air pump (20) and the air pipe (21). A micro air pressure sensor (26) is provided inside the gas chamber.

3. The UAV landing gear for geographic information mapping according to claim 2, characterized in that: The chamber (22) is provided with a reset spring (25), and the reset spring (25) is sleeved on the pressure column (23). The pressure column (23) is elastically connected to the block (19) through the reset spring (25).

4. The UAV landing gear for geographic information mapping according to claim 1, characterized in that: The locking assembly (10) includes a protective shell (29) and a servo motor (28) fixedly installed inside the wall of the thin rod (4). A worm (30) and a rotating shaft (31) are rotatably installed inside the protective shell (29). A worm wheel (32) is fixedly sleeved on the rotating shaft (31). The worm (30) is meshed with the worm wheel (32). One end of the worm (30) is fixedly connected to the output shaft end of the servo motor (28). An elastic pressure member (33) is provided at one end of the rotating shaft (31).

5. The UAV landing gear for geographic information mapping according to claim 4, characterized in that: The elastic pressure member (33) is composed of a central block (3301), a pressure block (3302), a guide groove (3303), a compression spring (3304), and a guide post (3305). The central part of the central block (3301) is fixedly connected to one end of the rotating shaft (31). Both sides of the central block (3301) are elastically connected to the pressure block (3302) through the compression spring (3304). The pressure block (3302) is fixedly connected to the guide post (3305). The guide post (3305) is connected to the guide groove (3303) opened on the central block (3301) with a clearance fit.

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