A topographic surveying device for civil engineering

Abstract

This invention discloses a topographic surveying device for civil engineering, relating to the field of topographic surveying technology. It includes a drone body, a surveying mechanism, and a correction mechanism. The surveying mechanism includes an inner cavity formed at the upper end of the drone body. A mounting plate is slidably connected to the inner wall of the inner cavity. A mounting column is fixedly connected to the upper end of the mounting plate. A measuring instrument is fixedly connected to the side wall of the mounting column. A wind pressure drive block is fixedly connected to the upper end of the mounting column. Multiple guide columns are fixedly connected to the bottom of the inner cavity, and the side walls of the multiple guide columns are slidably connected to the mounting plate. This invention employs a special streamlined design of the wind pressure drive block, utilizing Bernoulli's principle to allow the height of the measuring instrument to be continuously and dynamically adjusted according to wind speed. Through dynamic adjustment and a two-tiered protection mechanism with extreme storage, the operational weather window of the drone body is broadened, maximizing task continuity and operational efficiency while ensuring absolute equipment safety.

Description

Technical Field

[0001] This invention relates to the field of topographic surveying technology, and more particularly to a topographic surveying device for civil engineering. Background Technology

[0002] In the field of civil engineering, using drones equipped with surveying instruments for topographic mapping has become an important, efficient, and flexible method.

[0003] Currently, in actual field operations, drones often face complex weather environments, especially sudden crosswinds, which seriously affect the continuity of measurement operations, equipment safety, and data quality. Existing technologies have the following main shortcomings: First, when drones fly in strong winds, solid particles such as sand and dust carried by the wind can easily collide with and damage the exposed lenses of measuring instruments; second, crosswinds not only threaten equipment safety but also disrupt the flight stability of drones, causing the fuselage to tilt and shake, seriously affecting the accuracy of measurement data and flight safety; finally, the dusty environment in the field can easily contaminate the lenses of measuring instruments, affecting imaging and data quality. Summary of the Invention

[0004] To address the problems mentioned in the background section, the present invention adopts the following technical solution:

[0005] A topographic surveying device for civil engineering includes a drone body, a surveying mechanism, and a correction mechanism.

[0006] The measuring mechanism includes an inner cavity formed at the upper end of the UAV body. A mounting plate is slidably connected to the inner wall of the inner cavity. A mounting column is fixedly connected to the upper end of the mounting plate. A measuring instrument is fixedly connected to the side wall of the mounting column. A wind pressure driving block is fixedly connected to the upper end of the mounting column. Multiple guide columns are fixedly connected to the bottom of the inner cavity. The side walls of the multiple guide columns are slidably connected to the mounting plate. A spring is sleeved on the side wall of the guide column. The two ends of the spring are fixedly connected to the bottom of the inner cavity and the lower end of the mounting plate, respectively.

[0007] The correction mechanism includes four auxiliary slots located at the lower end of the UAV body, which penetrate the UAV body. A mounting block is fixedly connected to the inner wall of the auxiliary slot. A rotating shaft is rotatably connected to the lower end of the mounting block. Multiple auxiliary propellers are fixedly connected to the side wall of the rotating shaft. A micro motor is fixedly connected to the upper end of the mounting block. The output end of the micro motor passes through the mounting block and is fixedly connected to the rotating shaft.

[0008] Preferably, the correction mechanism further includes a balancing hollow sphere fixedly connected to the upper end of the UAV body. A universal joint is fixedly connected to the top of the balancing hollow sphere, and a conductive metal ball is fixedly connected to the lower end of the universal joint. Four arc-shaped electrode plates are fixedly connected to the inner wall of the balancing hollow sphere. The four arc-shaped electrode plates are arranged in a circular array with the balancing hollow sphere as the center. The conductive metal ball, the arc-shaped electrode plates, and the micro motor are electrically connected by wires.

[0009] Preferably, a resistance strip is fixedly embedded in the inner wall of the cavity, and a conductive block is fixedly embedded in the side wall of the mounting plate. The resistance strip and the conductive block are connected in series with a circuit consisting of a conductive metal ball, an arc-shaped electrode plate, and a micro motor through wires.

[0010] Preferably, the upper surface of the wind pressure drive block is a horizontal plane, and its lower surface is an arc-shaped surface.

[0011] Preferably, a cleaning mechanism is installed inside the inner cavity. The cleaning mechanism includes a cleaning groove formed on the inner wall of the inner cavity. A cleaning block is slidably connected to the inner wall of the cleaning groove. A liquid inlet chamber is formed inside the cleaning block. A cleaning sponge is fixedly connected to the side wall of the cleaning block. One end of the cleaning sponge extends into the liquid inlet chamber. The liquid inlet chamber is connected to the cleaning groove through a one-way liquid inlet hole. A liquid storage tank is fixedly connected to the side wall of the drone body. The cleaning groove is connected to the liquid storage tank through a one-way liquid inlet pipe.

[0012] Preferably, the cleaning mechanism further includes a squeezing block fixedly connected to the lower end of the measuring instrument, and a spring is fixedly connected between the inner wall of the cleaning tank and the cleaning block.

[0013] Preferably, the upper end of the cleaning block and the lower end of the squeezing block are both rounded.

[0014] Preferably, a recycling mechanism is installed in the inner cavity. The recycling mechanism includes a recycling groove formed on the inner wall of the inner cavity. A recycling box is slidably connected to the inner wall of the recycling groove. A drain hole is formed at the bottom of the recycling box. A drain channel corresponding to the drain hole is formed at the bottom of the recycling groove. A solenoid valve is installed on the inner wall of the drain hole.

[0015] Preferably, the recovery mechanism further includes a pneumatic chamber located inside the drone body. A sliding plug is slidably connected to the inner wall of the pneumatic chamber, and a connecting rod is fixedly connected to the side wall of the sliding plug. One end of the connecting rod extends into the cleaning tank and is fixedly connected to the cleaning block. The second spring is movably sleeved on the side wall of the connecting rod. The pneumatic chamber is connected to the recovery tank through a connecting pipe.

[0016] The present invention has the following beneficial effects:

[0017] 1. The special streamlined design of the wind pressure drive block utilizes Bernoulli's principle to enable the measuring instrument's height to be continuously and dynamically adjusted according to wind speed. It can maintain normal measurement in light winds, reduce the height to decrease wind resistance and optimize flight attitude in moderate to strong winds, and quickly and completely retract into the internal cavity to obtain all-round physical protection in strong winds. Through the two-level protection mechanism of dynamic adjustment and extreme retraction, the weather window for the operation of the UAV body is widened, maximizing the continuity of missions and operational efficiency while ensuring the absolute safety of the equipment.

[0018] 2. The purely mechanical tilt sensing system, composed of a balanced hollow sphere, a conductive metal sphere, and an arc-shaped electrode plate, can determine the tilt direction of the aircraft without delay and quickly adjust the flight attitude of the UAV. Furthermore, the tilt signal and the lifting position of the measuring instrument are linked through a resistor bar and a conductive block, which enables the auxiliary propeller power used for correction to automatically and linearly increase with the crosswind intensity. This achieves adaptive control for small corrections in light winds and large corrections in strong winds, making the recovery of flight attitude more accurate, efficient, and energy-saving, and improving the flight stability and safety of the UAV in turbulent conditions.

[0019] 3. The descent and storage action of the measuring instrument is linked with the cleaning mechanism. When the measuring instrument reaches its lowest point, the squeezing block triggers the movement of the cleaning block, and the hydraulic pressure generated by its sealing and sliding automatically delivers the cleaning fluid to the cleaning sponge. Thus, the lens is moistened and wiped simultaneously during the storage process. When the measuring instrument is under protection, maintenance is completed in a fully automatic manner, ensuring the cleanliness of the lens and guaranteeing the quality of the data source. At the same time, the linked pneumatically driven recycling box can automatically receive and store cleaning waste liquid, avoiding secondary pollution and demonstrating the environmental friendliness and integrity of the design. Attached Figure Description

[0020] Figure 1 This is a three-dimensional structural diagram of a topographic surveying device for civil engineering proposed in this invention;

[0021] Figure 2 for Figure 1 A bottom-view diagram of the mid-structure;

[0022] Figure 3 for Figure 1 Cross-sectional view of the middle structure;

[0023] Figure 4 for Figure 3 Enlarged schematic diagram of the structure at point A;

[0024] Figure 5 for Figure 3 Enlarged schematic diagram of the structure at point B;

[0025] Figure 6 for Figure 3 Enlarged schematic diagram of the structure at point C;

[0026] Figure 7 for Figure 3 Enlarged schematic diagram of the structure at point D;

[0027] Figure 8 This is a schematic diagram of the circuit connection consisting of a conductive metal ball, an arc-shaped electrode plate, a micro motor, a resistor strip, and a conductive block.

[0028] In the diagram: 1. UAV body; 2. Inner cavity; 3. Mounting plate; 4. Mounting column; 5. Measuring instrument; 6. Wind pressure drive block; 7. Guide column; 8. Spring 1; 9. Auxiliary groove; 10. Mounting block; 11. Rotating shaft; 12. Auxiliary propeller; 13. Micro motor; 14. Balance hollow ball; 15. Universal joint; 16. Conductive metal ball; 17. Arc-shaped electrode plate; 18. Resistance strip; 19. Conductive block; 20. Cleaning groove; 21. Cleaning block; 22. Liquid inlet chamber; 23. Cleaning sponge; 24. One-way liquid inlet hole; 25. Liquid storage tank; 26. One-way liquid inlet pipe; 27. Squeezing block; 28. Connecting rod; 29. ​​Spring 2; 30. Recovery groove; 31. Recovery box; 32. Drain hole; 33. Drainage channel; 34. Air pressure chamber; 35. Sliding plug; 36. Connecting pipe. Detailed Implementation

[0029] To make the above-mentioned objects, features, and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of the present invention. However, the present invention can be practiced in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0030] Reference Figures 1-8 A topographic surveying device for civil engineering includes a drone body 1, a surveying mechanism, and a correction mechanism.

[0031] The measuring mechanism includes an inner cavity 2 located at the top of the UAV body 1. An installation plate 3 is slidably connected to the inner wall of the inner cavity 2. An installation column 4 is fixedly connected to the upper end of the installation plate 3. A measuring instrument 5 is fixedly connected to the side wall of the installation column 4. A wind pressure drive block 6 is fixedly connected to the upper end of the installation column 4. The upper surface of the wind pressure drive block 6 is a horizontal plane, and its lower surface is an arc surface. Multiple guide columns 7 are fixedly connected to the bottom of the inner cavity 2. The side walls of the multiple guide columns 7 are slidably connected to the installation plate 3. A spring 8 is sleeved on the side wall of the guide column 7. The two ends of the spring 8 are fixedly connected to the bottom of the inner cavity 2 and the lower end of the installation plate 3, respectively.

[0032] Furthermore, by controlling the flight of the drone body 1, the measuring instrument 5 moves at high altitude to perform terrain measurement operations. However, in general civil engineering, when the drone body 1 encounters crosswinds due to environmental factors, the dust and sand particles carried by the crosswinds can easily damage the lens of the measuring instrument 5. In addition, strong crosswinds can also interfere with the flight attitude of the drone body 1, causing flight instability and affecting the measurement. Therefore, when the drone body 1 is carrying the measuring instrument 5 for flight measurement, if it encounters crosswinds, and the crosswinds flow through the wind pressure drive block 6, the airflow velocity at the lower end of the wind pressure drive block 6 will be higher than that at the upper end due to the arc-shaped design of the lower end of the wind pressure drive block 6. According to Bernoulli's theorem, when gas flows at the same height, the faster the flow velocity, the lower the pressure generated. This will cause pressure to be generated at both ends of the wind pressure drive block 6. A pressure difference is generated, and the pressure at the lower end of the wind pressure drive block 6 is less than that at its upper end. Under the action of the pressure difference, the wind pressure drive block 6 will move downward, driving the mounting column 4 and the measuring instrument 5 downward, which in turn drives the mounting plate 3 downward, compressing the spring 8. When the crosswind speed is low, the generated pressure cannot completely overcome the reaction force of the spring 8, causing the measuring instrument 5 to completely enter the inner cavity 2. Therefore, the measuring instrument 5 will drop a certain height at this time, but it can still maintain normal measurement. The drop in height of the measuring instrument 5 can effectively reduce wind resistance and reduce the impact on the flight stability of the UAV body 1. At this time, because the crosswind speed is low, the impact force of the dust and sand particles carried is not very large on the measuring instrument 5. Thus, the measuring instrument 5 can be outside the inner cavity 2 to carry out normal measurement, thereby maximizing the working window.

[0033] Furthermore, if a strong crosswind is encountered, the dust and sand particles carried by the crosswind have a strong impact force and may damage the lens of the measuring instrument 5. Therefore, under the action of a strong crosswind, the pressure generated is sufficient to completely press the measuring instrument 5 into the inner cavity 2. Thus, under the protection of the inner cavity 2, the dust and sand particles cannot hit the measuring instrument 5, which can effectively protect the measuring instrument 5.

[0034] It is worth mentioning that when the crosswind speed is within a certain range, the measuring instrument 5 will not enter the inner cavity 2. However, the height of the measuring instrument 5 will be dynamically adjusted according to the crosswind speed and intensity, which can reduce the impact of wind resistance within a certain range. Moreover, this dynamic adjustment allows the measuring instrument 5 to quickly enter the inner cavity 2 in the shortest time when encountering stronger crosswinds, thereby improving the response speed and reducing the impact of sand and gravel particles on it.

[0035] The correction mechanism includes four auxiliary slots 9 located at the lower end of the UAV body 1. The auxiliary slots 9 penetrate the UAV body 1. A mounting block 10 is fixedly connected to the inner wall of the auxiliary slot 9. A rotating shaft 11 is rotatably connected to the lower end of the mounting block 10. Multiple auxiliary propellers 12 are fixedly connected to the side wall of the rotating shaft 11. A micro motor 13 is fixedly connected to the upper end of the mounting block 10. The output end of the micro motor 13 passes through the mounting block 10 and is fixedly connected to the rotating shaft 11.

[0036] The correction mechanism also includes a balancing hollow sphere 14 fixedly connected to the upper end of the UAV body 1. A universal joint 15 is fixedly connected to the top of the balancing hollow sphere 14, and a conductive metal ball 16 is fixedly connected to the lower end of the universal joint 15. Four arc-shaped electrode plates 17 are fixedly connected to the inner wall of the balancing hollow sphere 14. The four arc-shaped electrode plates 17 are arranged in a ring array with the balancing hollow sphere 14 as the center. The conductive metal ball 16, the arc-shaped electrode plates 17 and the micro motor 13 are electrically connected by wires.

[0037] It should be noted that the conductive metal ball 16, the arc-shaped electrode plate 17 and the micro motor 13 are connected in series with a power supply through wires to power the circuit. The four arc-shaped electrode plates 17 and the four micro motors 13 corresponding to their positions are electrically connected through wires. By individually connecting the four arc-shaped electrode plates 17, the four micro motors 13 can be controlled individually.

[0038] Furthermore, when encountering crosswinds, the impact of the crosswinds may cause the UAV body 1 to tilt and deflect, thus making it impossible to maintain a stable flight attitude. Therefore, when the UAV body 1 tilts in any of the four directions (forward, backward, left, right), the conductive metal ball 16 inside the balancing hollow sphere 14 will deflect to the tilted side under the influence of gravity along with the universal joint 15. The conductive metal ball 16 will then contact the arc-shaped electrode plate 17 on the corresponding side, energizing and starting the micro motor 13 on the corresponding side. This will drive the shaft 11 to rotate, which in turn drives the auxiliary propeller 12 to rotate, generating thrust and causing the side to deflect in the opposite direction, adjusting the flight attitude and allowing the UAV body 1 to return to a basic level flight state. This ensures the stable flight of the UAV body 1, guaranteeing normal measurement and normal flight, and avoiding the risk of crashing. During the process of the UAV body 1 deflecting in the opposite direction and returning to level, the conductive metal ball 16 will gradually return to the center position of the balancing hollow sphere 14, and the micro motor 13 on the corresponding side will also be de-energized and stop rotating, ceasing to correct the deviation and avoiding over-correction.

[0039] It should be noted that since the conductive metal ball 16 can only contact the corresponding arc-shaped electrode plate 17 for correction when the UAV body 1 is tilted at a certain angle, the small-angle tilt of the UAV body 1 during flight is a normal flight attitude. Only when the offset angle is too large under the intervention of crosswind will it be corrected. Therefore, the horizontal flight attitude of the UAV body 1 can be dynamically changed within a certain tilt angle, which can meet the small-angle tilt of the UAV body 1 when turning.

[0040] A resistor strip 18 is fixedly embedded in the inner wall of the inner cavity 2, and a conductive block 19 is fixedly embedded in the side wall of the mounting plate 3. The resistor strip 18 and the conductive block 19 are connected in series with the circuit composed of the conductive metal ball 16, the arc-shaped electrode plate 17 and the micro motor 13 through wires.

[0041] It should be noted that, as Figure 8 As shown, each arc-shaped electrode plate 17 is connected in series with its corresponding micro motor 13 via a wire, and each group of arc-shaped electrode plates 17 and micro motors 13 are connected in parallel with each other. The power supply, conductive metal ball 16, resistor strip 18 and conductive block 19 are connected in series in the circuit via wires.

[0042] Furthermore, the stronger the crosswind, the more violent the deflection of the drone body 1 will be, and the greater the thrust required to correct the flight attitude in order to counteract the crosswind intensity. When the crosswind is stronger, the position of the mounting plate 3 in the inner cavity 2 will be lower, and the position of the conductive block 19 will be lower. Therefore, the resistance of the resistor strip 18 connected to the circuit will be smaller, and the current flowing through the micro motor 13 will be larger, so that the micro motor 13 will generate a faster rotation speed. In turn, the auxiliary propeller 12 will generate a faster rotation speed and generate stronger thrust to cope with the stronger crosswind and adjust the flight attitude of the drone body 1. Therefore, the entire device can automatically adjust the correction intensity according to the crosswind intensity, with a high degree of intelligence, can cope with changing environments, and has stronger robustness.

[0043] A cleaning mechanism is installed inside the inner cavity 2. The cleaning mechanism includes a cleaning groove 20 opened on the inner wall of the inner cavity 2. A cleaning block 21 is slidably connected to the inner wall of the cleaning groove 20. An inlet chamber 22 is opened in the cleaning block 21. A cleaning sponge 23 is fixedly connected to the side wall of the cleaning block 21. One end of the cleaning sponge 23 extends into the inlet chamber 22. The inlet chamber 22 is connected to the cleaning groove 20 through a one-way inlet hole 24. The one-way inlet hole 24 only allows the cleaning liquid in the cleaning groove 20 to enter the inlet chamber 22. A liquid storage tank 25 is fixedly connected to the side wall of the drone body 1. The liquid storage tank 25 stores cleaning liquid and has an inlet for adding cleaning liquid and a sealing cap (not shown in the figure) at its upper end. The cleaning groove 20 is connected to the liquid storage tank 25 through a one-way inlet pipe 26. The one-way inlet pipe 26 only allows the cleaning liquid in the liquid storage tank 25 to enter the cleaning groove 20.

[0044] The cleaning mechanism also includes a squeezing block 27 fixedly connected to the lower end of the measuring instrument 5, and a spring 29 fixedly connected between the inner wall of the cleaning tank 20 and the cleaning block 21.

[0045] The upper end of the cleaning block 21 and the lower end of the extrusion block 27 are both rounded.

[0046] Furthermore, as the measuring instrument 5 descends into the inner cavity 2, the squeezing block 27 also descends synchronously. The squeezing block 27 will first contact the cleaning block 21. Since the contact surfaces of the squeezing block 27 and the cleaning block 21 are rounded, the downward pressure of the squeezing block 27 will compress the cleaning block 21, causing it to move to the left side of the cleaning tank 20 (e.g., ...). Figure 6 As shown, the cleaning block 21 enters the cleaning tank 20. When the measuring instrument 5 is fully inserted into the inner cavity 2, the lens of the measuring instrument 5 is directly opposite the cleaning sponge 23. The measuring instrument 5 exerts slight pressure and sliding friction on the cleaning sponge 23. As the cleaning block 21 slides in the cleaning tank 20, it squeezes the cleaning liquid in the cleaning tank 20. Under pressure, the cleaning liquid is forced into the inlet cavity 22 through the one-way inlet hole 24. The cleaning sponge 23 absorbs the cleaning liquid. The slight pressure from the measuring instrument 5 and the sliding friction generated when the measuring instrument 5 moves allow the cleaning sponge 23 to wipe the lens of the measuring instrument 5, thereby cleaning the lens of the measuring instrument 5 and ensuring the cleanliness of the lens, thus ensuring the accuracy of the measurement data.

[0047] A recycling mechanism is installed inside the inner cavity 2. The recycling mechanism includes a recycling tank 30 opened on the inner wall of the inner cavity 2. A recycling box 31 is slidably connected to the inner wall of the recycling tank 30. A drain hole 32 is opened at the bottom of the recycling box 31. A drain channel 33 corresponding to the drain hole 32 is opened at the bottom of the recycling tank 30. A solenoid valve is installed on the inner wall of the drain hole 32.

[0048] It should be noted that the drain hole 32 and the drain channel 33 are initially aligned (e.g., Figure 7 (As shown).

[0049] The recovery mechanism also includes a pneumatic chamber 34 located inside the drone body 1. A sliding plug 35 is slidably connected to the inner wall of the pneumatic chamber 34. A connecting rod 28 is fixedly connected to the side wall of the sliding plug 35. One end of the connecting rod 28 extends into the cleaning tank 20 and is fixedly connected to the cleaning block 21. A spring 29 is movably sleeved on the side wall of the connecting rod 28. The pneumatic chamber 34 is connected to the recovery tank 30 through a connecting pipe 36.

[0050] It should be noted that a sealing ring is provided at the sliding connection between the connecting rod 28 and the drone body 1 to ensure a seal and prevent leakage of cleaning fluid in the cleaning tank 20.

[0051] Furthermore, when the cleaning block 21 slides, it drives the sliding plug 35 to slide to the left via the connecting rod 28, squeezing the air in the air pressure chamber 34 into the recycling tank 30 through the connecting pipe 36, pushing the recycling box 31 to move, causing part of the recycling box 31 to extend out, and the recycling box 31 to be directly below the cleaning sponge 23. This causes the cleaning liquid dripping from the cleaning sponge 23 to fall into the recycling box 31 for collection. When the measuring instrument 5 moves upward to reset, the cleaning block 21 lacks resistance and, under the action of the second spring 29, causes the cleaning block 21 to slide to the right to seal and reset (as shown). Figure 6 As shown), at this time, the cleaning fluid in the storage tank 25 will be drawn into the cleaning tank 20 through the one-way inlet pipe 26 for later use, and the cleaning block 21 will also drive the sliding plug 35 to move to the right and reset through the connecting rod 28. At this time, the air in the recovery tank 30 will be drawn back into the air pressure chamber 34 through the connecting pipe 36, and then the recovery box 31 will move to the left and reset. When the drone body 1 flies back to the ground, the solenoid valve in the drain hole 32 can be energized to open the drain hole 32, and then the cleaning fluid in the recovery box 31 will be discharged from the drone body 1 through the drain hole 32 and the drain channel 33.

[0052] It should be noted that after the recycling box 31 is moved to the right, the leftmost end of the recycling box 31 will not move to the right end of the drain channel 33. The inner bottom of the recycling box 31 can still block the drain channel 33, thereby ensuring the sealing of the internal space of the recycling tank 30.

[0053] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A topographic surveying device for civil engineering, comprising an unmanned aerial vehicle (UAV) body (1), characterized in that, It also includes a measuring mechanism and a correction mechanism; The measuring mechanism includes an inner cavity (2) opened at the upper end of the UAV body (1), an mounting plate (3) is slidably connected to the inner wall of the inner cavity (2), an mounting column (4) is fixedly connected to the upper end of the mounting plate (3), a measuring instrument (5) is fixedly connected to the side wall of the mounting column (4), a wind pressure drive block (6) is fixedly connected to the upper end of the mounting column (4), and multiple guide columns (7) are fixedly connected to the bottom of the inner cavity (2). The side walls of the multiple guide columns (7) are slidably connected to the mounting plate (3), and a spring (8) is sleeved on the side wall of the guide column (7). The two ends of the spring (8) are fixedly connected to the bottom of the inner cavity (2) and the lower end of the mounting plate (3) respectively. The correction mechanism includes four auxiliary slots (9) located at the lower end of the UAV body (1). The auxiliary slots (9) penetrate the UAV body (1). An installation block (10) is fixedly connected to the inner wall of the auxiliary slot (9). A rotating shaft (11) is rotatably connected to the lower end of the installation block (10). Multiple auxiliary propellers (12) are fixedly connected to the side wall of the rotating shaft (11). A micro motor (13) is fixedly connected to the upper end of the installation block (10). The output end of the micro motor (13) penetrates the installation block (10) and is fixedly connected to the rotating shaft (11).

2. The topographic surveying device for civil engineering according to claim 1, characterized in that, The correction mechanism also includes a balancing hollow sphere (14) fixedly connected to the upper end of the UAV body (1). A universal joint (15) is fixedly connected to the top of the balancing hollow sphere (14), and a conductive metal ball (16) is fixedly connected to the lower end of the universal joint (15). Four arc-shaped electrode plates (17) are fixedly connected to the inner wall of the balancing hollow sphere (14). The four arc-shaped electrode plates (17) are arranged in a ring array with the balancing hollow sphere (14) as the center. The conductive metal ball (16), the arc-shaped electrode plates (17) and the micro motor (13) are electrically connected by wires.

3. A topographic surveying device for civil engineering according to claim 2, characterized in that, The inner wall of the cavity (2) is fixedly embedded with a resistor strip (18), and the side wall of the mounting plate (3) is fixedly embedded with a conductive block (19). The resistor strip (18) and the conductive block (19) are connected in series with a circuit consisting of a conductive metal ball (16), an arc-shaped electrode plate (17), and a micro motor (13) through wires.

4. A topographic surveying device for civil engineering according to claim 1, characterized in that, The upper surface of the wind pressure drive block (6) is a horizontal surface, and its lower surface is an arc surface.

5. A topographic surveying device for civil engineering according to claim 1, characterized in that, A cleaning mechanism is installed in the inner cavity (2). The cleaning mechanism includes a cleaning groove (20) opened on the inner wall of the inner cavity (2). A cleaning block (21) is slidably connected to the inner wall of the cleaning groove (20). An inlet chamber (22) is opened in the cleaning block (21). A cleaning sponge (23) is fixedly connected to the side wall of the cleaning block (21). One end of the cleaning sponge (23) extends into the inlet chamber (22). The inlet chamber (22) is connected to the cleaning groove (20) through a one-way inlet hole (24). A liquid storage tank (25) is fixedly connected to the side wall of the drone body (1). The cleaning groove (20) is connected to the liquid storage tank (25) through a one-way inlet pipe (26).

6. A topographic surveying device for civil engineering according to claim 5, characterized in that, The cleaning mechanism also includes a squeezing block (27) fixedly connected to the lower end of the measuring instrument (5), and a spring (29) is fixedly connected between the inner wall of the cleaning tank (20) and the cleaning block (21).

7. A topographic surveying device for civil engineering according to claim 6, characterized in that, The upper end of the cleaning block (21) and the lower end of the squeezing block (27) are both rounded.

8. A topographic surveying device for civil engineering according to claim 6, characterized in that, The inner cavity (2) is equipped with a recycling mechanism, which includes a recycling groove (30) opened on the inner wall of the inner cavity (2). The inner wall of the recycling groove (30) is sealed and slidably connected to a recycling box (31). The bottom of the recycling box (31) is provided with a drain hole (32). The bottom of the recycling groove (30) is provided with a drain channel (33) corresponding to the drain hole (32). The inner wall of the drain hole (32) is equipped with a solenoid valve.

9. A topographic surveying device for civil engineering according to claim 8, characterized in that, The recovery mechanism also includes a pressure chamber (34) opened in the drone body (1). The inner wall of the pressure chamber (34) is sealed and slidably connected with a plug (35). The side wall of the plug (35) is fixedly connected with a connecting rod (28). One end of the connecting rod (28) extends into the cleaning tank (20) and is fixedly connected to the cleaning block (21). The second spring (29) is movably sleeved on the side wall of the connecting rod (28). The pressure chamber (34) is connected to the recovery tank (30) through a connecting pipe (36).

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