An unmanned aerial vehicle based engineering mapping device and method of use

Abstract

The application belongs to the technical field of unmanned aerial vehicle surveying and mapping, in particular to an engineering surveying and mapping device based on an unmanned aerial vehicle and a use method thereof, comprising an unmanned aerial vehicle body and a surveying and mapping instrument body arranged below the unmanned aerial vehicle body, further comprising a hollow placement cylinder, a fund-raising balloon, a first gas bottle, a first gas pipe, a second gas pipe, a first back-shaped air bag and a stall control for monitoring the attitude of the unmanned aerial vehicle body, the placement cylinder is fixedly installed at the top end of the unmanned aerial vehicle body, the fund-raising balloon is fixedly installed on the inner wall of the placement cylinder, the inner cavity of the fund-raising balloon is communicated with the inner cavity of the first back-shaped air bag through the first gas pipe, the first gas bottle is detachably installed in the interior of the unmanned aerial vehicle body, the output end of the first gas bottle is communicated with the first gas pipe through the second gas pipe, and the exterior of the second gas pipe is provided with an electromagnetic valve, through the cooperation of the above structures, the separation of the unmanned aerial vehicle body and the surveying and mapping instrument body can reduce the weight, and the protection effect is further improved.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) surveying technology, specifically an engineering surveying device and its usage method based on UAVs. Background Technology

[0002] Unmanned aerial vehicle (UAV) engineering surveying refers to a technical method that uses UAVs as carriers to acquire aerial data through various types of sensors, enabling rapid and high-precision mapping, 3D modeling, and data processing of ground features. UAV surveying engineering mainly includes UAV equipment and safety, data acquisition and processing, measurement technology, and applications, and has been widely used in land surveying, resource management, urban planning, transportation, environmental protection, and other fields.

[0003] For example, Chinese patent CN109367805A describes a surveying drone with a rotating camera. By using a catapult parachute, the drone can be protected from severe damage due to a high-speed fall in the event of an emergency during high-altitude operations, and it can also ensure that the drone will not injure people on the ground due to a high-speed fall.

[0004] However, when a drone runs out of power and is unable to return and crashes, it may flip or tilt due to the influence of airflow. At this time, the drone's center of gravity may change. When the drone's center of gravity is not directly below, even if a parachute is installed, it will affect the opening and protection effect of the parachute, causing the parachute to fail to open properly or to be unstable after opening, thus affecting the protection effect.

[0005] Therefore, the present invention provides an engineering surveying device and its usage method based on unmanned aerial vehicles (UAVs). Summary of the Invention

[0006] In order to overcome the shortcomings of the prior art, at least one technical problem raised in the background art is solved.

[0007] The technical solution adopted by the present invention to solve its technical problem is: an engineering surveying device based on a drone, comprising a drone body and a surveying instrument body disposed below the drone body;

[0008] It also includes a hollow placement tube, a calibrating balloon, a first air cylinder, a first air tube, a second air tube, a first loop-shaped airbag, and a stall control for monitoring the attitude of the UAV itself;

[0009] The placement tube is fixedly installed on the top of the drone body, the adjustment balloon is fixedly installed on the inner wall of the placement tube, the inner cavity of the adjustment balloon is connected to the inner cavity of the first loop-shaped air bag through the first air tube, the first air cylinder is detachably installed inside the drone body, the output end of the first air cylinder is connected to the first air tube through the second air tube, and a solenoid valve is provided on the outside of the second air tube.

[0010] The stall control includes a circuit board and an inertial measurement unit, an accelerometer, and a microcontroller integrated on the circuit board. The inertial measurement unit and accelerometer monitor the attitude and velocity changes of the UAV body and transmit the data to the microcontroller to control the opening and closing of the solenoid valve.

[0011] Furthermore, a hollow connecting cylinder is fixedly installed at one end of the surveying instrument body near the UAV body, and an installation cylinder for sliding insertion of the connecting cylinder is fixedly installed at one end of the UAV body near the surveying instrument body.

[0012] The inner wall of the mounting cylinder is elastically connected with a locking block, and the outer wall of the connecting cylinder is provided with a slot for the locking block to be inserted.

[0013] A second air cylinder is slidably installed at one end of the surveying instrument body close to the drone body. The second air cylinder is located below the first loop-shaped airbag. The sliding of the second air cylinder is controlled by the expansion of the first loop-shaped airbag. A third air tube is slidably inserted into the output end of the second air cylinder. The other end of the third air tube is fixedly connected to a pressure airbag for pressing the block. A buffer umbrella is set above the pressure airbag.

[0014] Furthermore, a top plate corresponding to the locking block is fixedly installed on the outer wall of the top pressure airbag.

[0015] Furthermore, a limit ring is slidably installed on the top outer wall of the surveying instrument body, the outer wall of the second gas cylinder is connected to the inner wall of the limit ring by internal and external thread engagement, a limit block is fixedly installed on the outer wall of the limit ring, and the bottom end of the limit block is connected to the inside of the surveying instrument body by a return spring.

[0016] Furthermore, a second circular airbag is fixedly installed at the bottom of the surveying instrument body, and a fourth air tube is fixedly connected to the outer wall of the second circular airbag. The other end of the fourth air tube is connected to the third air tube.

[0017] Furthermore, a movable plate is slidably installed on the inner wall of the connecting cylinder, and the movable plate is positioned above the top pressure airbag. A transmission block is fixedly installed on the side wall of the movable plate. A transmission groove for the transmission block to slide is opened on the inner wall of the connecting cylinder. The bottom end of the transmission block is fixedly connected to the inside of the transmission groove through a top pressure spring. The top end of the connecting cylinder is fixedly connected to the buffer umbrella.

[0018] Furthermore, the side wall of the drone body is provided with a movable groove for the first gas cylinder to slide. A suction cup for adsorbing the first gas cylinder is fixedly installed inside the movable groove. A top plate rod for pressing the suction cup is slidably installed inside the drone body. An extension rod is fixedly connected to the top of the top plate rod, and the other end of the extension rod extends out of the top outer wall of the drone body.

[0019] Furthermore, a pressing plate is fixedly connected to the end of the extension rod away from the drone body, and a connecting spring is fixedly connected to the outer wall of the end of the pressing plate facing the drone body. The other end of the connecting spring is fixedly connected to the outer wall of the drone body.

[0020] Furthermore, an elastic cover plate is slidably connected to the inner wall of the connecting cylinder. The side wall of the elastic cover plate is interference-fitted with the inner wall of the connecting cylinder. A connecting rope is fixedly connected to the top of the elastic cover plate, and the other end of the connecting rope is fixedly connected to the bottom outer wall of the drone body.

[0021] A method for using an unmanned aerial vehicle (UAV)-based engineering surveying device, the method comprising the following steps:

[0022] S1: The inertial measurement unit and accelerometer monitor the fall signal of the drone body and transmit it to the microcontroller to control the opening of the solenoid valve. At this time, the first gas cylinder can deliver compressed gas to the inner cavity of the adjustment balloon through the first air tube and make it expand, helping the drone body adjust its attitude to a vertical landing. The compressed gas is delivered to the first U-shaped airbag through the second air tube to make it expand, which can improve the protection effect of the drone body.

[0023] S2: The first inflatable airbag presses down on the second air cylinder. At this time, compressed gas enters the airbag through the third air pipe, causing it to expand and drive the top plate to press down on the block, thus separating the surveying instrument body from the drone body. The buffer umbrella set inside the connecting cylinder buffers the separated surveying instrument body. At the same time, the fourth air pipe delivers compressed gas to the second inflatable airbag, which can improve the protection effect of the surveying instrument body.

[0024] The beneficial effects of this invention are as follows:

[0025] 1. The present invention discloses an engineering surveying device and method based on a drone, which detects the fall of the drone body through a stall control and controls the opening of a solenoid valve. At this time, the first gas cylinder can deliver compressed gas through the first air tube to the inner cavity of the adjustment balloon and cause it to expand, helping the drone body adjust its attitude to a vertical landing. The compressed gas is delivered through the second air tube to the first U-shaped airbag to expand, which can improve the protection effect of the drone body.

[0026] 2. The engineering surveying device and method based on UAV described in this invention uses an inflated first circular airbag to press against a second air cylinder. At this time, compressed gas enters the pressing airbag through a third air pipe, causing it to expand and drive the top plate to press against the locking block, thus separating the surveying instrument body from the UAV body. The buffer umbrella set inside the connecting cylinder buffers the separated surveying instrument body. At the same time, the fourth air pipe delivers compressed gas to the second circular airbag to inflate it. By reducing the weight, the protection effect of the UAV body and the surveying instrument body can be further improved. Attached Figure Description

[0027] The invention will now be further described with reference to the accompanying drawings.

[0028] Figure 1 This is a perspective view of the present invention;

[0029] Figure 2 This is a schematic diagram of the structure of the adjustment balloon in this invention;

[0030] Figure 3 In this invention Figure 2 Enlarged view of point A in the image;

[0031] Figure 4 This is a schematic diagram of the structure of the surveying instrument in this invention;

[0032] Figure 5 In this invention Figure 4 Enlarged view of point B in the image;

[0033] Figure 6 In this invention Figure 4 Enlarged view of point C in the image;

[0034] Figure 7 This is a schematic diagram of the first circular airbag pressing against the second air cylinder in this invention;

[0035] Figure 8 This is a schematic diagram of the top plate rod in this invention;

[0036] Figure 9 This is a schematic diagram of the unfolding of the adjustment balloon in this invention;

[0037] Figure 10 This is a schematic diagram of the unfolding of the buffer umbrella in this invention;

[0038] Figure 11 This is a schematic diagram of the structure of the elastic cover plate in this invention;

[0039] Figure 12 This is a schematic diagram of the method flow in this invention.

[0040] In the diagram: 1. UAV body; 2. Surveying instrument body; 3. Placement cylinder; 4. Adjustment balloon; 5. First gas cylinder; 6. First air pipe; 7. Circuit board; 8. First loop-shaped airbag; 9. Movable slot; 10. Four air pipes; 11. Second gas cylinder; 12. Top pressure airbag; 13. Top plate rod; 14. Suction cup; 15. Extension rod; 16. Connecting spring; 17. Pressing plate; 18. Buffer umbrella; 19. Mounting cylinder; 20. Second loop-shaped airbag; 21. Second air pipe; 22. Solenoid valve; 23. Limiting ring; 24. Limiting block; 25. Connecting cylinder; 26. Transmission block; 27. Locking block; 28. Top plate; 29. ​​Movable plate; 30. Elastic cover plate; 31. Connecting rope; 32. Third air pipe. Detailed Implementation

[0041] To make the technical means, creative features, objectives and effects of this invention easier to understand, the invention will be further described below in conjunction with specific embodiments.

[0042] Example 1: As Figures 1 to 10 As shown in the figure, an engineering surveying device based on a drone according to an embodiment of the present invention includes a drone body 1 and a surveying instrument body 2 disposed below the drone body 1.

[0043] It also includes a hollow placement tube 3, a calibrating balloon 4, a first gas cylinder 5, a first air tube 6, a second air tube 21, a first loop-shaped airbag 8, and a stall control for monitoring the attitude of the UAV body 1.

[0044] The placement tube 3 is fixedly installed on the top of the drone body 1, and the adjustment balloon 4 is fixedly installed on the inner wall of the placement tube 3. An installation plate is fixedly installed below the adjustment balloon 4. The side wall of the installation plate is fixedly connected to the inner wall of the placement tube 3. The installation plate is used to limit the position of the adjustment balloon 4 and prevent it from detaching from the inside of the placement tube 3 after it expands. The top of the adjustment balloon 4 is equipped with a deflation knob. By turning this knob, the gas inside the adjustment balloon 4 can be emptied. The adjustment balloon 4 can then be folded back and placed back into the placement tube 3.

[0045] The inner cavity of the adjustment balloon 4 is connected to the inner cavity of the first loop-shaped air bag 8 through the first air pipe 6. The first air cylinder 5 is detachably installed inside the drone body 1. The output end of the first air cylinder 5 is connected to the first air pipe 6 through the second air pipe 21. A solenoid valve 22 is provided on the outside of the second air pipe 21.

[0046] The first air cylinder 5 is located on one side of the drone body 1. The output end of the first air cylinder 5 is a common push-button valve. By pressing the first air cylinder 5, the valve is opened, and the compressed air inside the first air cylinder 5 is discharged under air pressure. When the first air cylinder 5 is installed inside the drone body 1, the output end of the first air cylinder 5 extends into the inside of the second air tube 21. When pressed, the first air cylinder 5 is in the open state. The inner wall of the second air tube 21 can be blocked by the solenoid valve 22. At this time, by controlling the solenoid valve 22 to open the second air tube 21, the compressed air can enter the interior of the adjustment balloon 4 and the first loop-shaped air bag 8 and cause it to expand.

[0047] The adjustment balloon 4 can release compressed gas from the first gas cylinder 5 into the second air tube 21. At this time, the compressed gas can enter the inner cavity of the first air tube 6 through the second air tube 21, causing the first loop-shaped airbag 8 and the adjustment balloon 4 to inflate. After the adjustment balloon 4 unfolds, it can quickly adjust the attitude of the drone body 1 due to power failure and fall, so that the adjustment balloon 4 is above and the drone body 1 is below. In addition, the adjustment balloon 4 is surrounded by an umbrella-shaped wrapping to increase the contact area with the air, which can further increase the drag during the fall, thereby slowing down the fall speed of the drone body 1. Furthermore, the first loop-shaped airbag 8 at the bottom of the drone body 1 can also reduce the impact force generated when the drone body 1 lands, further improving the protection effect of the drone body 1.

[0048] The stall control includes a circuit board 7 and an inertial measurement unit, an accelerometer, and a microcontroller integrated on the circuit board 7. The inertial measurement unit and the accelerometer monitor the attitude and speed changes of the UAV body 1 and transmit the data to the microcontroller to control the opening and closing of the solenoid valve 22. The UAV body 1 is equipped with an emergency power supply. When the UAV body 1 runs out of power and crashes, the stall control can use the emergency power supply to monitor the attitude and speed of the UAV body 1.

[0049] When the drone body 1 runs out of power and cannot return, the inertial measurement unit and accelerometer detect the attitude and speed changes of the drone body 1 and organize them into corresponding signals, which are then transmitted to the microcontroller. At this time, the microcontroller can control the solenoid valve 22 to open, and the compressed gas inside the first gas cylinder 5 can enter the interior of the attitude adjustment balloon 4 and the first loop-shaped airbag 8 through the first air pipe 6, and expand simultaneously. When the attitude adjustment balloon 4 is deployed, the attitude of the drone body 1 can be quickly controlled. The attitude adjustment balloon 4 is located above and the drone body 1 is located below. The deployed attitude adjustment balloon 4 can slow down the descent speed. By adjusting the falling attitude of the drone body 1 after deployment, the drone body 1 can be slowed down. In conjunction with the first loop-shaped airbag 8, the drone body 1 can be protected.

[0050] A hollow connecting cylinder 25 is fixedly installed at one end of the surveying instrument body 2 near the drone body 1. An installation cylinder 19 for sliding insertion of the connecting cylinder 25 is fixedly installed at one end of the drone body 1 near the surveying instrument body 2. The connecting cylinder 25 at the top of the surveying instrument body 2 can be inserted into the installation cylinder 19 at the bottom of the drone body 1. The outer wall of the connecting cylinder 25 fits against the inner wall of the installation cylinder 19.

[0051] The inner wall of the mounting cylinder 19 is elastically connected to a locking block 27. The interior of the mounting cylinder 19 has a receiving groove for the locking block 27 to slide. A first spring is provided between the locking block 27 and the receiving groove. The first spring always presses the locking block 27 so that it extends out of the receiving groove. The outer wall of the connecting cylinder 25 has a slot for the locking block 27 to be inserted. The end of the locking block 27 near the connecting cylinder 25 is inclined. When the connecting cylinder 25 is inserted into the mounting cylinder 19, the top of the connecting cylinder 25 can press the inclined surface of the locking block 27. The locked block 27, which is pressed, can retract into the receiving groove. At this time, the first spring deforms and stores elastic potential energy. When the slot on the outer wall of the mounting cylinder 19 corresponds to the position of the locking block 27, the first spring releases elastic potential energy and pushes the locking block 27 into the inner cavity of the slot, limiting the position of the mounting cylinder 19. At this time, the surveying instrument body 2 can be fixed to the bottom of the UAV body 1.

[0052] A second gas cylinder 11 is slidably mounted on one end of the surveying instrument body 2 near the drone body 1. The second gas cylinder 11 is positioned below the first circular airbag 8. The second gas cylinder 11 has a circular cross-section and its output end is also designed for push-to-release. The sliding of the second gas cylinder 11 is controlled by the expansion of the first circular airbag 8. When the first circular airbag 8 expands, it can press down on the second gas cylinder 11, causing it to slide inside the surveying instrument body 2. A third air tube 32 is slidably inserted into the output end of the second gas cylinder 11. The other end of the third air tube 32 is fixedly connected to a pressure airbag 12 for pressing down the locking block 27. A buffer umbrella 18 is positioned above the pressure airbag 12. The second gas cylinder 11 adopts a common push-to-release valve design. When the second gas cylinder 11 is pressed down, it is in the open state, and the compressed gas inside the second gas cylinder 11 can be released under pressure. Under the action of the air duct 32, the air is delivered into the interior of the third air duct 32 and guided by the third air duct 32. The air duct 32 then enters the interior of the pressure bladder 12 and expands. When the pressure bladder 12 expands, it can press against the card block 27 that is engaged with the card slot, causing it to contract into the inner cavity of the receiving groove. The drone body 1 falls at different speeds than the connecting tube 25 under the buffer of the air duct 4. At this time, the connecting tube 25 can detach from the interior of the mounting tube 19 under the action of gravity, so that the surveying instrument body 2 separates from the drone body 1. When the surveying instrument body 2 falls, the buffer umbrella 18 set inside the connecting tube 25 can open with the help of the airflow to slow down the falling speed of the surveying instrument body 2. By separating the drone body 1 and the surveying instrument body 2, the weight can be reduced, thereby reducing the energy during the fall and improving the protection effect of the air duct 4 on the drone body 1 and the buffer umbrella 18 on the surveying instrument body 2.

[0053] The outer wall of the pressure airbag 12 is fixedly equipped with a top plate 28 corresponding to the locking block 27. The top plate 28 on the outer wall of the pressure airbag 12 can compensate for the distance of the wall thickness of the connecting cylinder 25. When the pressure airbag 12 expands, it is easier to press the locking block 27 into the inner cavity of the receiving groove, thereby improving the separation effect between the surveying instrument body 2 and the UAV body 1.

[0054] A limiting ring 23 is slidably installed on the top outer wall of the surveying instrument body 2. The outer wall of the second gas cylinder 11 is connected to the inner wall of the limiting ring 23 by internal and external thread engagement. A limiting block 24 is fixedly installed on the outer wall of the limiting ring 23. The bottom end of the limiting block 24 is connected to the inside of the surveying instrument body 2 through a return spring. When the limiting ring 23 is pressed, the limiting ring 23 can drive the limiting block 24 to squeeze the return spring. The limit block 24 can be reset by releasing the elastic potential energy of the return spring.

[0055] The top of the surveying instrument body 2 is provided with a limiting groove for the limiting ring 23 to slide. By pressing the limiting ring 23, it can slide inside the surveying instrument body 2. The limiting groove can limit the sliding trajectory of the limiting ring 23. When installing the second gas cylinder 11, the second gas cylinder 11 can be installed into the inner wall of the limiting ring 23 by means of threads. At this time, the second gas cylinder 11 can avoid the risk of falling off when the drone body 1 moves the surveying instrument body 2. At the same time, the threaded installation method can also facilitate the replacement of the used second gas cylinder 11.

[0056] A second loop-shaped airbag 20 is fixedly installed at the bottom of the surveying instrument body 2. A fourth air pipe 10 is fixedly connected to the outer wall of the second loop-shaped airbag 20. The other end of the fourth air pipe 10 is connected to the third air pipe 32. When the second gas cylinder 11 is pressed by the inflated first loop-shaped airbag 8, the high-pressure gas in the second gas cylinder 11 can enter the interior of the fourth air pipe 10 through the third air pipe 32. The second loop-shaped airbag 20 connected to the fourth air pipe 10 will then inflate to protect the bottom of the surveying instrument body 2. When the surveying instrument body 2 is separated from the UAV body 1, the protection effect of the surveying instrument body 2 can be further improved by the cooperation of the buffer parachute 18 and the second loop-shaped airbag 20.

[0057] A movable plate 29 is slidably installed on the inner wall of the connecting cylinder 25. The movable plate 29 is positioned above the top pressure airbag 12. A transmission block 26 is fixedly installed on the side wall of the movable plate 29. A transmission groove is opened on the inner wall of the connecting cylinder 25 for the transmission block 26 to slide. The bottom end of the transmission block 26 is fixedly connected to the inside of the transmission groove through a top pressure spring. The top end of the connecting cylinder 25 is fixedly connected to the buffer umbrella 18. When the connecting cylinder 25 is separated from the mounting cylinder 19, the movable plate 29 can be pushed out from the inside of the connecting cylinder 25 under the action of the top pressure spring. Under the action of the top pressure spring, a certain instantaneous potential energy is increased, which further improves the opening efficiency of the buffer umbrella 18. It can also provide a certain counter-thrust force to help the connecting cylinder 25 slide out from the inner wall of the mounting cylinder 19.

[0058] The side wall of the drone body 1 is provided with a movable groove 9 for the first gas cylinder 5 to slide. The outer wall of the first gas cylinder 5 is set as a plane. A suction cup 14 for adsorbing the first gas cylinder 5 is fixedly installed inside the movable groove 9. When the first gas cylinder 5 is pushed into the inner wall of the movable groove 9, one end of the first gas cylinder 5 will contact and squeeze with the suction cup 14. After the air between the suction cup 14 and the outer wall of the first gas cylinder 5 is squeezed out, the suction cup 14 can then adsorb the first gas cylinder 5, thus completing the installation of the first gas cylinder 5.

[0059] Inside the drone body 1, a top plate rod 13 for pressing the suction cup 14 is slidably installed. The top plate rod 13 is provided with a ring larger than the diameter of the suction cup 14. By controlling the top plate rod 13 to slide on the inner wall of the drone body 1, the ring provided on the top plate rod 13 can press the suction cup 14. Since the ring pushes the corner of the suction cup 14, it is easy to push the suction cup 14 to separate from the first gas cylinder 5. At this time, the first gas cylinder 5 can be taken out and replaced after use.

[0060] An extension rod 15 is fixedly connected to the top of the top plate rod 13. The other end of the extension rod 15 extends out of the top outer wall of the drone body 1. By pressing the top of the extension rod 15, the top plate rod 13 can be controlled to slide inside the drone body 1 to press against the suction cup 14. When the first gas cylinder 5 needs to be installed, the extension rod 15 needs to be pulled upward. At this time, the top plate rod 13 will not block the suction cup 14, making it easier to adsorb the outer wall of the first gas cylinder 5.

[0061] The end of the extension rod 15 away from the drone body 1 is fixedly connected to a pressing plate 17. The outer wall of the end of the pressing plate 17 facing the drone body 1 is fixedly connected to a connecting spring 16. The other end of the connecting spring 16 is fixedly connected to the outer wall of the drone body 1. The connecting spring 16 can maintain the pressing plate 17 with a pressing tendency. When the pressing plate 17 is applied downward, the top plate rod 13 can be driven to press the suction cup 14, causing it to separate from the first gas cylinder 5. By the reset of the connecting spring 16, the pressing plate 17 is pressed, and the top plate rod 13 can release the pressure on the suction cup 14, allowing the first gas cylinder 5 to be reinstalled.

[0062] Example 2: Figure 11 As shown in Example 1, another embodiment of the present invention is as follows:

[0063] An elastic cover plate 30 is slidably connected to the inner wall of the connecting cylinder 25. The side wall of the elastic cover plate 30 is interference-fitted with the inner wall of the connecting cylinder 25. A connecting rope 31 is fixedly connected to the top of the elastic cover plate 30. The other end of the connecting rope 31 is fixedly connected to the bottom outer wall of the UAV body 1. The elastic cover plate 30 is located inside the mounting cylinder 19.

[0064] When it is necessary to install the surveying instrument body 2 and the drone body 1, the buffer parachute 18 needs to be reinserted into the connecting cylinder 25, and the elastic cover plate 30 set at the bottom of the drone body 1 needs to be inserted into the inner wall of the connecting cylinder 25. The elastic cover plate 30, which is interference-fitted with the inside of the connecting cylinder 25, can block the elastically set movable plate 29. When the drone body 1 and the surveying instrument body 2 are separated, until the connecting cylinder 25 is completely separated from the mounting cylinder 19, the elastic cover plate 30 is pulled out from the inside of the connecting cylinder 25 under the action of the connecting rope 31. At this time, the movable plate 29 can then pop the buffer parachute 18 out from the inside of the connecting cylinder 25 under the action of the top pressure spring, effectively reducing the risk of the buffer parachute 18 being blocked by the mounting cylinder 19 when it opens, and further improving the use effect of the buffer parachute 18.

[0065] like Figure 12 As shown, a method for using an engineering surveying device based on a drone, the method employing the aforementioned drone-based engineering surveying device, includes the following steps:

[0066] S1: The fall signal of the drone body 1 is monitored by the inertial measurement unit and the accelerometer and transmitted to the microcontroller, which controls the solenoid valve 22 to open. At this time, the first gas cylinder 5 can deliver compressed gas to the inner cavity of the adjustment balloon 4 through the first air pipe 6 and make it expand, which helps the drone body 1 adjust its attitude to a vertical landing. The compressed gas is delivered to the first loop-shaped airbag 8 through the second air pipe 21 and made to expand, which can improve the protection effect of the drone body 1.

[0067] S2: The first inflatable airbag 8 presses against the second air cylinder 11. At this time, compressed gas enters the pressure airbag 12 through the third air pipe 32, causing it to expand and drive the top plate 28 to press against the locking block 27, causing the surveying instrument body 2 to separate from the drone body 1. The buffer umbrella 18 set inside the connecting cylinder 25 buffers the separated surveying instrument body 2. At the same time, the fourth air pipe 10 delivers compressed gas to the second inflatable airbag 20 to expand it, which can improve the protection effect of the surveying instrument body 2.

[0068] Working principle: The stall control transmits the fall signal of the drone body 1 to the microcontroller and controls the solenoid valve 22 to open. At this time, the first gas cylinder 5 can deliver compressed gas to the inner cavity of the adjustment balloon 4 through the first air pipe 6 and make it expand, which helps the drone body 1 adjust its attitude to a vertical landing and slows down the fall. The compressed gas is delivered to the first loop-shaped airbag 8 through the second air pipe 21 to make it expand, which can improve the protection effect of the drone body 1.

[0069] The first inflatable airbag 8 presses against the second air cylinder 11. At this time, compressed gas enters the pressure airbag 12 through the third air pipe 32, causing it to expand and drive the top plate 28 to press against the locking block 27, causing the surveying instrument body 2 to separate from the drone body 1. The buffer umbrella 18 set inside the connecting cylinder 25 buffers the separated surveying instrument body 2. At the same time, the fourth air pipe 10 delivers compressed gas to the second inflatable airbag 20 to expand it, which can improve the protection effect of the surveying instrument body 2.

[0070] The terms "front," "back," "left," "right," "top," and "bottom" all refer to the figures in the accompanying drawings. Figure 1 Based on the perspective of the observer, the side of the device facing the observer is defined as the front, the left side of the observer is defined as the left, and so on.

[0071] In the description of this invention, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this invention.

[0072] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. An engineering surveying device based on a drone, comprising a drone body (1) and a surveying instrument body (2) disposed below the drone body (1). Its features are: It also includes a hollow placement tube (3), a calibrating balloon (4), a first gas cylinder (5), a first air tube (6), a second air tube (21), a first circular airbag (8), and a stall control for monitoring the attitude of the UAV body (1); The placement tube (3) is fixedly installed on the top of the drone body (1), the accelerator balloon (4) is fixedly installed on the inner wall of the placement tube (3), the inner cavity of the accelerator balloon (4) is connected to the inner cavity of the first loop-shaped air bag (8) through the first air pipe (6), the first air cylinder (5) is detachably installed inside the drone body (1), the output end of the first air cylinder (5) is connected to the first air pipe (6) through the second air pipe (21), and a solenoid valve (22) is provided on the outside of the second air pipe (21). The stall control includes a circuit board (7) and an inertial measurement unit, an accelerometer and a microcontroller integrated on the circuit board (7). The inertial measurement unit and the accelerometer monitor the attitude and speed changes of the UAV body (1) and transmit them to the microcontroller to control the opening and closing of the solenoid valve (22). The surveying instrument body (2) is fixedly installed with a hollow connecting cylinder (25) at one end near the UAV body (1), and the UAV body (1) is fixedly installed with an installation cylinder (19) for sliding insertion of the connecting cylinder (25). The inner wall of the mounting cylinder (19) is elastically connected with a locking block (27), and the outer wall of the connecting cylinder (25) is provided with a slot for the locking block (27) to be inserted. The surveying instrument body (2) has a second gas cylinder (11) slidably installed at one end near the UAV body (1). The second gas cylinder (11) is located below the first loop-shaped airbag (8). The sliding of the second gas cylinder (11) is controlled by the expansion of the first loop-shaped airbag (8). The output end of the second gas cylinder (11) is slidably connected to a third air tube (32). The other end of the third air tube (32) is fixedly connected to a pressure airbag (12) for pressing the pressure block (27). A buffer umbrella (18) is provided above the pressure airbag (12).

2. The engineering surveying device based on an unmanned aerial vehicle (UAV) according to claim 1, characterized in that: The outer wall of the top pressure airbag (12) is fixedly fitted with a top plate (28) corresponding to the locking block (27).

3. The engineering surveying device based on an unmanned aerial vehicle (UAV) according to claim 2, characterized in that: A limiting ring (23) is slidably installed on the outer wall of the top of the surveying instrument body (2). The outer wall of the second gas cylinder (11) is connected to the inner wall of the limiting ring (23) by internal and external thread. A limiting block (24) is fixedly installed on the outer wall of the limiting ring (23). The bottom end of the limiting block (24) is connected to the inside of the surveying instrument body (2) by a reset spring.

4. The engineering surveying device based on an unmanned aerial vehicle (UAV) according to claim 3, characterized in that: The bottom of the surveying instrument body (2) is fixedly installed with a second loop-shaped airbag (20), and the outer wall of the second loop-shaped airbag (20) is fixedly connected with a fourth air tube (10). The other end of the fourth air tube (10) is connected to the third air tube (32).

5. The engineering surveying device based on an unmanned aerial vehicle (UAV) according to claim 4, characterized in that: A movable plate (29) is slidably installed on the inner wall of the connecting cylinder (25). The movable plate (29) is positioned above the top pressure airbag (12). A transmission block (26) is fixedly installed on the side wall of the movable plate (29). A transmission groove is provided on the inner wall of the connecting cylinder (25) for the transmission block (26) to slide. The bottom end of the transmission block (26) is fixedly connected to the inside of the transmission groove through a top pressure spring. The top end of the connecting cylinder (25) is fixedly connected to the buffer umbrella (18).

6. The engineering surveying device based on an unmanned aerial vehicle (UAV) according to claim 5, characterized in that: The side wall of the drone body (1) is provided with a movable groove (9) for the first gas cylinder (5) to slide. A suction cup (14) for adsorbing the first gas cylinder (5) is fixedly installed inside the movable groove (9). A top plate rod (13) for pressing the suction cup (14) is slidably installed inside the drone body (1). An extension rod (15) is fixedly connected to the top of the top plate rod (13). The other end of the extension rod (15) extends out of the top outer wall of the drone body (1).

7. The engineering surveying device based on an unmanned aerial vehicle (UAV) according to claim 6, characterized in that: The extension rod (15) is fixedly connected to a pressing plate (17) at one end away from the drone body (1). A connecting spring (16) is fixedly connected to the outer wall of the pressing plate (17) facing the drone body (1). The other end of the connecting spring (16) is fixedly connected to the outer wall of the drone body (1).

8. The engineering surveying device based on an unmanned aerial vehicle (UAV) according to claim 7, characterized in that: The inner wall of the connecting cylinder (25) is slidably connected to an elastic cover plate (30). The side wall of the elastic cover plate (30) is interference-fitted with the inner wall of the connecting cylinder (25). The top end of the elastic cover plate (30) is fixedly connected to a connecting rope (31). The other end of the connecting rope (31) is fixedly connected to the bottom outer wall of the UAV body (1).

9. A method for using an engineering surveying device based on an unmanned aerial vehicle (UAV), wherein the method employs the engineering surveying device based on an UAV as described in any one of claims 1-8, characterized in that: Includes the following steps: S1: The fall signal of the UAV body (1) is monitored by the inertial measurement unit and the acceleration sensor and transmitted to the microcontroller and the solenoid valve (22) is opened. At this time, the first gas cylinder (5) can deliver compressed gas to the inner cavity of the adjustment balloon (4) through the first air pipe (6) and make it expand, which helps the attitude of the UAV body (1) to adjust to vertical landing. The compressed gas is delivered to the first loop airbag (8) through the second air pipe (21) and made to expand, which can improve the protection effect of the UAV body (1). S2: The first circular airbag (8) presses against the second air cylinder (11) through expansion. At this time, the compressed gas enters the pressure airbag (12) through the third air pipe (32), causing it to expand and drive the top plate (28) to press against the block (27), so that the surveying instrument body (2) is separated from the drone body (1). The buffer umbrella (18) set inside the connecting tube (25) buffers the separated surveying instrument body (2). At the same time, the fourth air pipe (10) delivers compressed gas to the second circular airbag (20) to expand it, which can improve the protection effect of the surveying instrument body (2).

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