Unmanned aerial vehicle measuring device for measuring terrain

Abstract

The invention discloses an unmanned aerial vehicle measuring device for measuring terrain, and relates to the technical field of unmanned aerial vehicles, the unmanned aerial vehicle measuring device comprises an unmanned aerial vehicle main body, the bottom of the unmanned aerial vehicle main body is fixedly provided with two undercarriages, the outer surface wall of the unmanned aerial vehicle main body is fixedly provided with a group of propellers, and the top of the unmanned aerial vehicle main body is fixedly provided with a storage box. According to the unmanned aerial vehicle, the high-pressure air storage tank, the electric three-way valve and the second air pipeline form an inflation system, meanwhile, a trigger device composed of a first piston, a second piston, a clamping block and other structures in the storage box is activated when the unmanned aerial vehicle falls, the electric three-way valve is started, air in the high-pressure air storage tank is rapidly injected into the storage box, and the folding parachute is pushed to pop out; therefore, falling impact force is relieved, physical damage to equipment caused by crash is reduced, equipment maintenance and replacement cost is reduced, integrity and safety of task data such as surveying and mapping and investigation can be guaranteed, and damage to nearby personnel caused by falling of the unmanned aerial vehicle is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and specifically to an unmanned aerial vehicle measuring device for terrain measurement. Background Technique

[0002] An unmanned aerial vehicle is an unpiloted aircraft that is controlled by a radio remote control device and a self - contained program control device, or is completely or intermittently autonomously operated by an on - vehicle computer. It can perform diverse tasks such as reconnaissance and surveillance, mapping and exploration, environmental monitoring, agricultural plant protection, logistics distribution, film shooting, disaster relief, and target strike. It has significant advantages such as small size, strong mobility, flexible deployment, low cost, and adaptability to complex and dangerous environments, and is widely used in multiple fields such as military, civilian, and commercial.

[0003] Currently, most unmanned aerial vehicle measuring devices are not equipped with parachutes. This defect is prominent when operating in complex terrains. When the unmanned aerial vehicle encounters power failure, electronic malfunction, or sudden strong wind, the fuselage without a buffer will directly make a hard landing. The precision measuring equipment carried is extremely vulnerable to damage under the impact, and situations such as lens fragmentation, chip de - soldering, and gear jamming are likely to occur. The stored terrain data will also be lost due to physical damage to the storage module, resulting in mission interruption and missing data in key areas, and requiring a second flight to re - measure, which will cause problems such as extended project cycle and increased costs. When crashing, the high - speed rotating carbon fiber propeller blades will also break and fly, forming sharp ballistic fragments, posing a fatal risk of laceration and puncture to ground personnel. Summary of the Invention

[0004] The purpose of the present invention is to provide an unmanned aerial vehicle measuring device for terrain measurement, which can effectively slow down the descending speed by promptly ejecting an internal parachute at the moment of falling, so as to solve the problems raised in the above background.

[0005] To achieve the above purpose, the present invention provides the following technical solution: An unmanned aerial vehicle measuring device for terrain measurement, including an unmanned aerial vehicle main body. Two landing gears () are fixedly installed at the bottom of the unmanned aerial vehicle main body. A group of propellers are fixedly installed on the outer surface wall of the unmanned aerial vehicle main body. A storage box is fixedly installed on the top of the unmanned aerial vehicle main body. Four air outlet holes one are opened on the inner surface wall of the storage box. Four installation slots one are opened on the top of the storage box. A piston one is movably inserted into the inner surface wall of each of the four installation slots one. A group of installation slots two are opened on the inner surface wall of each of the four installation slots one. A spring one is fixedly installed on one side of the inner wall of each of the four groups of installation slots two. A clamping block is fixedly installed on one side of the outer wall of each of the four groups of spring ones, and the inner surface wall of each of the four groups of installation slots two is movably inserted with the outer surface wall of the clamping block. A piston two is movably sleeved between the outer surface walls of the four clamping blocks, and the outer surface walls of the four piston twos are movably inserted into the inside of the piston one. An air outlet hole two is opened on one side of the outer wall of each of the four piston twos.

[0006] Preferably, springs two are fixedly installed on the tops of the four pistons two, and the tops of the four springs two are fixedly connected to the inner wall tops of the piston one. One air outlet three is provided on one side of the outer walls of the four pistons one, and a set of moving holes are provided on the outer surfaces of the four pistons one, and the inner surfaces of the four sets of moving holes are movably inserted with the outer surfaces of the clamping blocks. Springs three are fixedly installed on the bottoms of the four pistons one, and the bottoms of the four springs three are fixedly connected to the inner wall bottoms of the mounting grooves one. Fixing rods are fixedly installed between the inner surfaces of the four mounting grooves one.

[0007] Preferably, reset turntables are fixedly sleeved on the outer surfaces of the four fixing rods, connecting force arms are fixedly sleeved on the outer surfaces of the four reset turntables, and the bottoms of the four connecting force arms are in contact with the tops of the piston one. One set of shaft holes is provided on the outer surfaces of the four connecting force arms, a rotating shaft is movably inserted between the inner surfaces of the four sets of shaft holes, moving wheels are fixedly sleeved on the outer surfaces of the four rotating shafts, and a flow dividing plate is fixedly inserted into the inner wall of the storage box.

[0008] Preferably, a folding parachute is arranged on the top of the flow dividing plate, two top covers are movably sleeved on the outer surface of the storage box, and one set of sliding grooves is provided on the inner surfaces of the two top covers, and sliding blocks are movably embedded in the inner surfaces of the two sets of sliding grooves.

[0009] Preferably, springs four are fixedly installed on one side of the inner walls of the two sets of sliding grooves, and the outer sides of the two sets of springs four are fixedly connected to the outer sides of the sliding blocks, and the outer surfaces between the two sets of sliding blocks are fixedly connected to the outer surface of the storage box. One set of positioning holes is provided on the tops of the two top covers, and the inner surfaces of the two sets of positioning holes are movably inserted with the outer surfaces of the moving wheels.

[0010] Preferably, an electric turntable one is fixedly installed at the bottom of the UAV main body, a support one is fixedly installed at the bottom of the electric turntable one, and an electric turntable two is fixedly installed on one side of the outer wall of the support one.

[0011] Preferably, a support two is fixedly installed on one side of the outer wall of the electric turntable two, a support three is fixedly installed on one side of the outer wall of the electric turntable two, and a camera is fixedly installed on one side of the outer wall of the electric turntable three.

[0012] Preferably, sealing rubber strips are adhered to one side of the outer walls of the two top covers, and the outer surfaces of the two sealing rubber strips are in contact with each other. A high-pressure gas storage tank is fixedly installed on one side of the outer wall of the storage box, and the output end of the high-pressure gas storage tank is fixedly communicated with an electric three-way valve.

[0013] Preferably, the output end of the electric three-way valve is fixedly communicated with a gas pipeline one, and the outer surface of the gas pipeline one is fixedly inserted into the inside of the storage box. The output end of the electric three-way valve is fixedly communicated with a gas pipeline two.

[0014] Preferably, the output end of the second gas pipeline is fixedly communicated with an airbag, and the top of the airbag is adhesively connected to the bottom of the UAV body.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0016] 1. In the present invention, the high-pressure gas storage tank, the electric three-way valve and the second gas pipeline constitute an inflation system. At the same time, the trigger device composed of structures such as the first piston, the second piston and the clamping block in the storage box is activated when the UAV falls. The electric three-way valve is started to quickly inject the gas in the high-pressure gas storage tank into the storage box, pushing the folding parachute to pop out, so as to slow down the falling impact force, reduce the physical damage of the equipment caused by crashing, reduce the equipment maintenance and replacement costs, and can also ensure the integrity and security of the task data such as surveying and reconnaissance, and reduce the harm caused by the UAV falling to the nearby personnel.

[0017] 2. In the present invention, the rotating mechanism composed of the first electric turntable, the second electric turntable and the third electric turntable can drive the camera to flexibly rotate in three directions of pitch, roll and yaw, and can offset the influence of crosswind and terrain undulation on the shooting angle in real time, ensure the accuracy of the measurement data, and improve the quality and efficiency of task execution.

[0018] 3. In the present invention, when the UAV falls into water, the electric three-way valve switches the connection to quickly inject the gas in the high-pressure gas storage tank into the airbag, causing it to expand rapidly, lifting the UAV to float on the water surface, avoiding the core components such as the fuselage, motor, battery and flight control system from being damaged by water immersion, facilitating the operator to quickly locate and recover the equipment, and saving the search time and labor cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is the main view structure three-dimensional diagram in a UAV measuring device for measuring terrain of the present invention;

[0020] Figure 2 It is the plan view in a UAV measuring device for measuring terrain of the present invention;

[0021] Figure 3 It is the partial structure top view in a UAV measuring device for measuring terrain of the present invention;

[0022] Figure 4 It is the partial structure sectional plan view in a UAV measuring device for measuring terrain of the present invention;

[0023] Figure 5 It is the enlarged view of structure A in a UAV measuring device for measuring terrain of the present invention;

[0024] Figure 6 It is the partial structure splitting schematic diagram in a UAV measuring device for measuring terrain of the present invention;

[0025] Figure 7 This is a top - down exploded view of a partial structure in an unmanned aerial vehicle (UAV) measurement device for measuring terrain according to the present invention;

[0026] Figure 8 This is a bottom view of a partial structure in an unmanned aerial vehicle (UAV) measurement device for measuring terrain according to the present invention;

[0027] Figure 9 This is a bottom - up exploded view of a partial structure in an unmanned aerial vehicle (UAV) measurement device for measuring terrain according to the present invention;

[0028] Figure 10 This is a three - dimensional view of a partial structure in an unmanned aerial vehicle (UAV) measurement device for measuring terrain according to the present invention;

[0029] Figure 11 This is a top - down three - dimensional view of a partial structure in an unmanned aerial vehicle (UAV) measurement device for measuring terrain according to the present invention.

[0030] In the figure: 1. UAV main body; 2. Landing gear; 3. Propeller; 4. Storage box; 5. First air outlet; 6. First installation groove; 7. First piston; 8. Second installation groove; 9. First spring; 10. Clamping block; 11. Second piston; 12. Second air outlet; 13. Second spring; 14. Third air outlet; 15. Movable hole; 16. Third spring; 17. Fixed rod; 18. Reset turntable; 19. Connecting force arm; 20. Axle hole; 21. Rotating shaft; 22. Movable wheel; 23. Flow - dividing plate; 24. Folding parachute; 25. Top cover; 26. Sliding groove; 27. Slider; 28. Fourth spring; 29. Positioning hole; 30. First electric turntable; 31. First bracket; 32. Second electric turntable; 33. Second bracket; 34. Third electric turntable; 35. Camera; 36. Sealing rubber strip; 37. High - pressure gas storage tank; 38. Electric three - way valve; 39. First gas pipeline; 40. Second gas pipeline; 41. Airbag. Detailed implementation manners

[0031] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0032] Embodiment 1: Refer to Figure 1 - Figure 11As shown in the figure, the present invention provides a drone measurement device for measuring terrain, including a drone main body 1. Two landing gears 2 are fixedly installed at the bottom of the drone main body 1. A group of propellers 3 are fixedly installed on the outer surface wall of the drone main body 1. A storage box 4 is fixedly installed on the top of the drone main body 1. Four air outlet holes 5 are opened on the inner surface wall of the storage box 4. Four installation grooves 6 are opened on the top of the storage box 4. A piston 7 is movably inserted into the inner surface wall of each of the four installation grooves 6. A group of installation grooves 8 are opened on the inner surface wall of each of the four installation grooves 6. A first spring 9 is fixedly installed on one side of the inner wall of each of the four groups of installation grooves 8. A clamping block 10 is fixedly installed on one side of the outer wall of each of the four groups of first springs 9. And the inner surface wall of each of the four groups of installation grooves 8 is movably inserted with the outer surface wall of the clamping block 10. A piston 11 is movably sleeved between the outer surface walls of each of the four groups of clamping blocks 10. And the outer surface walls of the four pistons 11 are movably inserted into the inside of the piston 7. An air outlet hole 12 is opened on one side of the outer wall of each of the four pistons 11. A second spring 13 is fixedly installed on the top of each of the four pistons 11. And the tops of the four second springs 13 are fixedly connected to the top of the inner wall of the piston 7. An air outlet hole 14 is opened on one side of the outer wall of each of the four pistons 7. A group of movable holes 15 are opened on the outer surface wall of each of the four pistons 7. And the inner surface wall of each of the four groups of movable holes 15 is movably inserted with the outer surface wall of the clamping block 10. A third spring 16 is fixedly installed on the bottom of each of the four pistons 7. And the bottoms of the four third springs 16 are fixedly connected to the bottom of the inner wall of the installation groove 6. A fixing rod 17 is fixedly installed between the inner surface walls of each of the four installation grooves 6. A reset turntable 18 is fixedly sleeved on the outer surface wall of each of the four fixing rods 17. A connecting force arm 19 is fixedly sleeved on the outer surface wall of each of the four reset turntables 18. And the bottoms of the four connecting force arms 19 are in contact with the top of the piston 7. A group of shaft holes 20 are opened on the outer surface wall of each of the four connecting force arms 19. A rotating shaft 21 is movably inserted between the inner surface walls of each of the four groups of shaft holes 20. A movable wheel 22 is fixedly sleeved on the outer surface wall of each of the four rotating shafts 21. A flow dividing plate 23 is fixedly inserted into the inner surface wall of the storage box 4. A folding parachute 24 is arranged on the top of the flow dividing plate 23. Two top covers 25 are movably sleeved on the outer surface wall of the storage box 4. A group of sliding grooves 26 are opened on the inner surface wall of each of the two top covers 25. A slider 27 is movably embedded in the inner surface wall of each of the two groups of sliding grooves 26. A fourth spring 28 is fixedly installed on one side of the inner wall of each of the two groups of sliding grooves 26. And the outer side of the outer wall of each of the two groups of fourth springs 28 is fixedly connected to the outer side of the outer wall of the slider 27. And the outer surface walls between the two groups of sliders 27 are fixedly connected to the outer surface wall of the storage box 4. A group of positioning holes 29 are opened on the top of each of the two top covers 25. And the inner surface walls of each of the two groups of positioning holes 29 are movably inserted with the outer surface wall of the movable wheel 22;

[0033] Sealing rubber strips 36 are adhered to one side of the outer walls of the two top covers 25, and the outer surface walls of the two sealing rubber strips 36 are in contact with each other.

[0034] In this embodiment, when the UAV is working, the UAV body 1 drives the four propellers 3 to start rotating, thereby generating an updraft to drive the UAV to rise and start measuring. When the UAV suddenly fails and falls, the electric three-way valve 38 starts to start, so that the high-pressure gas storage tank 37 is connected with the gas pipeline 1 39. At this time, the high-pressure gas inside the high-pressure gas storage tank 37 will come to the inside of the gas pipeline 1 39 under the action of pressure. The gas pipeline 1 39 transports the gas to the bottom of the installation groove 1 6. As the gas at the bottom of the installation groove 1 6 continues to accumulate, the pressure continues to rise, and the internal piston 1 7 and piston 2 11 are subjected to an upward thrust. The piston 1 7 is limited by the block 10 at this time, so that it remains fixed, and the piston 2 11 inserted in the piston 1 7 is pushed by the airflow, squeezing The spring 13 is compressed and begins to rise. The air outlet 15 will be at the same height as the air outlet 12, which is convenient for air flow to pass through. Since the inclined surface at the bottom of the block 10 contacts the piston 17, the block 10 cannot limit the piston 11, and when the piston 11 rises, the contact portion with the inclined surface of the block 10 pushes the block 10 outward, so that the block 10 squeezes the spring 9. The inclined surface of the block 10 also comes to the inside of the movable hole 15 of the piston 7. As the position of the block 10 changes, the piston 7 can no longer be limited. After the piston 7 is pushed up by the air flow, it begins to stretch the spring 3 16 at the bottom, and further promotes its displacement with the help of the inclined surface of the block 10. At this time, the block 10 is completely retracted into the installation groove 28. As the piston 17 rises, it will push the connecting force arm 19 to the top. The first end rises, making it rotate with the fixed rod 17 and the reset turntable 18 as the fulcrum. The reset turntable 18 is similar to the bearing structure and is a double-layer structure. A spring is arranged inside, which can drive the connecting force arm 19 to rotate and then reset. A section close to the piston 17 is used as the power arm end. During the rising process, it will drive the resistance arm end at the other end to rotate and descend, and retract into the installation groove 28. When the resistance arm end of the connecting force arm 19 moves, it will drive the internal rotating shaft 21 and the movable wheel 22 to move. The movable wheel 22 is subjected to force and will drive the rotating shaft 21 to rotate inside the shaft hole 20, replacing the sliding friction with the rolling friction, so as to facilitate the movable wheel 22 to slide out of the positioning hole 29. At this time, the movable wheel 22 will first push the top cover 25 to the center position, and the two top covers 25 will be adhered to one side of the outer wall. The sealing rubber strip 36 can not only improve the sealing performance of the storage box 4, but also has a certain elasticity, so that the two top covers 25 can be close to each other within a certain range. With the displacement of the top cover 25, space is provided for the movement of the movable wheel 22. As the movable wheel 22 slides out of the positioning hole 29 and the top cover 25 is not limited, the stretched spring four 28 begins to shrink, driving the top cover 25 to move outward, so that the foldable parachute 24 inside the storage box 4 can be ejected. At this time, the slider 27 will slide inside the slide groove 26. The two cooperate with each other to avoid the deviation of the movement direction of the top cover 25. At the same time, with the rise of the piston 7, the air outlet hole 2 12 and the air outlet hole 3 14 will be driven to coincide with the air outlet hole 1 5. At this time, the gas accumulated inside the installation groove 1 6,It is discharged to the bottom of the inner wall of the storage box 4 through three air outlets. When the gas continues to rise, the flow dividing plate 23 can make the air flow evenly diffuse, thereby improving the ejection effect of the folding parachute 24. When the upward air flow contacts the folding parachute 24 in the storage box 4, the folding parachute 24 is ejected, so as to quickly reduce the descending speed of the drone, which can reduce the damage caused by the crash of the equipment, reduce the maintenance cost, and avoid mission interruption or data loss caused by the crash of the drone, reduce the time and cost of redeployment and repeated measurement, and reduce casualties caused by factors such as propeller splashing and battery explosion during falling.,

[0035] Embodiment 2: As shown in Figure 1 , Figure 2 and Figure 10 , a first electric turntable 30 is fixedly installed at the bottom of the drone body 1. A first bracket 31 is fixedly installed at the bottom of the first electric turntable 30. A second electric turntable 32 is fixedly installed on one side of the outer wall of the first bracket 31. A second bracket 33 is fixedly installed on one side of the outer wall of the second electric turntable 32. A third electric turntable 34 is fixedly installed on one side of the outer wall of the second bracket 33. A camera 35 is fixedly installed on one side of the outer wall of the third electric turntable 34.

[0036] In this embodiment, when the camera 35 is working, the first electric turntable 30, the second electric turntable 32 and the third electric turntable 34 can drive it to rotate freely, control the rotation of the camera 35 in three axial directions of pitch, roll and yaw, and offset in real time the situations such as the tilt of the fuselage caused by crosswind and the change of pitch angle caused by terrain undulation of the drone, effectively improving the accuracy of the measurement results of the drone.

[0037] Embodiment 3: As shown in Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 8 and Figure 11 , a high-pressure gas storage tank 37 is fixedly installed on one side of the outer wall of the storage box 4. The output end of the high-pressure gas storage tank 37 is fixedly communicated with an electric three-way valve 38. The output end of the electric three-way valve 38 is fixedly communicated with a first gas pipeline 39, and the outer surface of the first gas pipeline 39 is fixedly inserted into the inside of the storage box 4. The output end of the electric three-way valve 38 is fixedly communicated with a second gas pipeline 40. The output end of the second gas pipeline 40 is fixedly communicated with an airbag 41, and the top of the airbag 41 is adhesively connected to the bottom of the drone body 1.

[0038] In this embodiment, when the gas of the folding parachute 24 inside the storage box 4 pops out, the electric three-way valve 38 will respond quickly and cut off the connection with the first gas pipeline 39 in time, so as to reserve a part of the high-pressure gas inside the high-pressure gas storage tank 37. When the UAV is about to land on the water surface, the electric three-way valve 38 is started again, so that the high-pressure gas storage tank 37 is connected with the second gas pipeline 40. Subsequently, the residual high-pressure air inside the high-pressure gas storage tank 37 advances through the second gas pipeline 40 and reaches the inside of the airbag 41, causing the airbag 41 to expand rapidly, ensuring that the UAV floats on the water surface, preventing important components such as the fuselage, motor, battery, and flight control system from being damaged due to long-term immersion in water, reducing the cost of equipment maintenance or replacement, and the UAV floating on the water surface is also easier to be discovered and recovered.

[0039] The working principle of the entire mechanism is as follows: When the drone starts operating, the drone body 1 drives the four propellers 3 to rotate at high speed, and the generated upward airflow pushes the fuselage into the air. Immediately afterwards, the measurement task is carried out. During the operation, the mounted camera 35 relies on the electric turntable one 30, the electric turntable two 32, and the electric turntable three 34 to achieve flexible rotation in the three axes of pitch, roll, and yaw. This design can offset the tilt of the fuselage caused by crosswinds in real time, as well as the change in pitch angle caused by terrain undulations. If the drone suddenly fails and falls, the electric three-way valve 38 is immediately activated, connecting the high-pressure gas storage tank 37 and the gas pipeline one 39. The high-pressure gas is transported through the pipeline to the bottom of the installation groove one 6. As the air pressure increases, the piston one 7 and the piston two 11 inside are subjected to an upward thrust. Due to the limiting effect of the catch 10, the piston one 7 remains fixed, while the piston two 11 squeezes the spring two 13 and moves upward. When the piston two 11 rises to contact the inclined surface of the catch 10, it pushes the catch 10 to compress the spring one 9, causing it to disengage from the limit of the piston one 7. The unconstrained piston one 7 rises under the action of the airflow, stretching the spring three 16 and further pushing the catch 10 to contract into the installation groove two 8. The rise of the piston one 7 drives the connecting force arm 19 to rotate with the fixed rod 17 as the fulcrum. While the power arm end rises, the resistance arm end descends and retracts into the installation groove two 8. During this process, the connecting force arm 19 drives the rotating shaft 21 and the movable wheel 22 to move. The movable wheel 22 rotates in the shaft hole 20 through rolling friction and slides out from the positioning hole 29. The two top covers 25 mounted on the storage box 4, with the sealing rubber strips 36 adhered to their outer walls providing sealing and elastic buffering, move closer to the center under the thrust of the movable wheel 22, creating a movement space for it. After the movable wheel 22 slides out, the spring four 28 contracts, driving the top cover 25 to expand outward, ejecting the folding parachute 24 inside the storage box 4. At the same time, the rise of the piston one 7 causes the air outlet one 5, the air outlet two 12, and the air outlet three 14 to coincide, and the gas in the installation groove one 6 is discharged through the three air outlets, evenly diffused by the flow dividing plate 23, boosting the rapid deployment of the folding parachute 24, slowing down the falling speed of the drone, reducing the risk of equipment damage, minimizing maintenance costs, avoiding mission interruption and data loss, and at the same time avoiding safety hazards such as propeller splashing and battery explosion. When the folding parachute 24 is ejected, the electric three-way valve 38 quickly cuts off the connection with the gas pipeline one 39, retaining part of the high-pressure gas in the high-pressure gas storage tank 37. If the drone is about to fall into the water, the electric three-way valve 38 is activated again, connecting the high-pressure gas storage tank 37 and the gas pipeline two 40, and the remaining high-pressure air is injected into the airbag 41, causing it to expand rapidly. The airbag 41 ensures that the drone floats on the water surface, preventing the core components such as the fuselage, motor, battery, and flight control system from being damaged by immersion in water, reducing equipment repair and replacement costs. The drone in the floating state is more easily discovered and recovered, ensuring equipment and data security.

[0040] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. An unmanned aerial vehicle measuring device for measuring terrain, comprising an unmanned aerial vehicle body (1), characterized in that: Two landing gears (2) are fixedly mounted on the bottom of the drone body (1), a set of propellers (3) are fixedly mounted on the outer wall of the drone body (1), a storage box (4) is fixedly mounted on the top of the drone body (1), four air outlet holes (5) are opened on the inner wall of the storage box (4), four installation slots (6) are opened on the top of the storage box (4), pistons (7) are movably inserted into the inner walls of the four installation slots (6), and a set of installation holes (7) are opened on the inner walls of the four installation slots (6). The four groups of mounting grooves (8) are provided with springs (9) fixedly mounted on one side of the inner wall of each of the four groups of mounting grooves (8), and blocks (10) are fixedly mounted on one side of the outer wall of each of the four groups of springs (9), and the inner surface walls of the four groups of mounting grooves (8) are movably inserted with the outer surface walls of the blocks (10), pistons (11) are movably sleeved between the outer surfaces of the four groups of blocks (10), and the outer surfaces of the four pistons (11) are movably inserted in the interior of the pistons (7), and air outlet holes (12) are opened on one side of the outer walls of the four pistons (11).

2. The unmanned aerial vehicle measuring device for measuring terrain according to claim 1, characterized in that: The tops of the four pistons (11) are all fixedly mounted with springs (13), and the tops of the four springs (13) are all fixedly connected to the top of the inner wall of the piston (7); one side of the outer wall of the four pistons (7) is provided with an air outlet hole (14); the outer wall of the four pistons (7) is all provided with a group of movable holes (15), and the inner walls of the four groups of movable holes (15) are all movably inserted with the outer wall of the block (10); the bottoms of the four pistons (7) are all fixedly mounted with springs (16), and the bottoms of the four springs (16) are all fixedly connected to the bottom of the inner wall of the mounting groove (6); and a fixing rod (17) is fixedly mounted between the inner walls of the four mounting grooves (6).

3. The unmanned aerial vehicle measuring device for measuring terrain according to claim 2, characterized in that: The outer walls of the four fixed rods (17) are all fixedly sleeved with a reset turntable (18), the outer walls of the four reset turntables (18) are all fixedly sleeved with a connecting force arm (19), and the bottoms of the four connecting force arms (19) are in contact with the top of the piston (7), the outer walls of the four connecting force arms (19) are all opened with a group of shaft holes (20), and the inner walls of the four groups of shaft holes (20) are all movably inserted with a rotating shaft (21), the outer walls of the four rotating shafts (21) are all fixedly sleeved with a movable wheel (22), and the inner wall of the storage box (4) is fixedly inserted with a diverter plate (23).

4. The unmanned aerial vehicle measuring device for measuring terrain according to claim 3, characterized in that: A folding parachute (24) is arranged on the top of the diverter plate (23); two top covers (25) are movably sleeved on the outer wall of the storage box (4); a group of slide grooves (26) are respectively provided on the inner walls of the two top covers (25); and sliders (27) are movably embedded in the inner walls of the two groups of slide grooves (26).

5. The unmanned aerial vehicle measuring device for measuring terrain according to claim 4, characterized in that: A spring four (28) is fixedly installed on one side of the inner wall of the two groups of the slide grooves (26), and one side of the outer wall of the two groups of spring four (28) is fixedly connected to one side of the outer wall of the slider (27), and the outer walls of the two groups of sliders (27) are fixedly connected to the outer wall of the storage box (4). A group of positioning holes (29) are opened on the top of the two top covers (25), and the inner walls of the two groups of positioning holes (29) are movably inserted into the outer wall of the movable wheel (22).

6. The unmanned aerial vehicle measuring device for measuring terrain according to claim 1, characterized in that: An electric turntable 1 (30) is fixedly mounted on the bottom of the drone body (1), a bracket 1 (31) is fixedly mounted on the bottom of the electric turntable 1 (30), and an electric turntable 2 (32) is fixedly mounted on one side of the outer wall of the bracket 1 (31).

7. The unmanned aerial vehicle measuring device for measuring terrain according to claim 6, characterized in that: A bracket 2 (33) is fixedly mounted on one side of the outer wall of the electric turntable 2 (32), an electric turntable 3 (34) is fixedly mounted on one side of the outer wall of the bracket 2 (33), and a camera (35) is fixedly mounted on one side of the outer wall of the electric turntable 3 (34).

8. The unmanned aerial vehicle measuring device for measuring terrain according to claim 5, characterized in that: A sealing rubber strip (36) is adhered to one side of the outer wall of the two top covers (25), and the outer walls of the two sealing rubber strips (36) are in contact with each other. A high-pressure gas storage tank (37) is fixedly installed on one side of the outer wall of the storage box (4), and the output end of the high-pressure gas storage tank (37) is fixedly connected to an electric three-way valve (38).

9. The unmanned aerial vehicle measuring device for measuring terrain according to claim 8, characterized in that: The output end of the electric three-way valve (38) is fixedly connected to a gas pipeline one (39), and the outer wall of the gas pipeline one (39) is fixedly inserted into the interior of the storage box (4). The output end of the electric three-way valve (38) is fixedly connected to a gas pipeline two (40).

10. The unmanned aerial vehicle measuring device for measuring terrain according to claim 9, characterized in that: The output end of the second gas pipeline (40) is fixedly connected to an air bag (41), and the top of the air bag (41) and the bottom of the drone body (1) are adhered to each other.

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