A folding rotor unmanned aerial vehicle special for field geological exploration

Abstract

The application relates to the technical field of unmanned planes, in particular to a folding rotor unmanned plane special for field geological exploration, which comprises an unmanned plane, the unmanned plane comprises a fuselage and wings, the fuselage is provided with a damping assembly, and the damping assembly comprises a base, a supporting leg, a bottom plate, a lifting shaft and an air bag. The folding rotor unmanned plane special for field geological exploration can damp the fuselage through the cooperative action of a reset spring, a ring-shaped cylinder closed gas and an air bag, the reset spring can directly buffer the vertical impact force when the fuselage falls to the ground, the vibration is reduced to be conducted to the inside of the fuselage, the ring-shaped cylinder and a ring-shaped plate form a closed cavity, the ring-shaped plate is moved up to compress the internal gas when falling to the ground, the vibration energy is consumed by using the gas damping effect, meanwhile, the air bag is extruded to generate flexible buffering, residual vibration is further absorbed, and the impact vibration when the unmanned plane falls on the apron is offset in multiple layers.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a folding rotary-wing UAV for field geological exploration. Background Technology

[0002] In the complex working environment of field geological exploration, with its varied terrain, ravines, and mountains, and harsh access conditions, traditional manual surveying methods often suffer from numerous drawbacks such as limited scope, low efficiency, and high operational risks. However, drones, with their significant advantages of high mobility, flexible operation, and wide adaptability, have become a core, efficient, and convenient surveying device in geological exploration, playing a crucial and irreplaceable role. Unrestricted by complex terrain, they can easily traverse rugged and dangerous areas such as steep slopes, canyons, dense forests, and cliffs, quickly reaching remote and dangerous areas inaccessible to personnel. Equipped with high-definition cameras, remote sensing mapping, and other specialized equipment, they can stably complete tasks such as large-scale panoramic image capture, 3D terrain modeling, and point information recording. They accurately collect key geological data such as topography, rock strata distribution, and geological structures, significantly improving the efficiency and accuracy of field exploration, effectively reducing the safety hazards and labor intensity of manual fieldwork, and providing solid and reliable data support for geological analysis, disaster investigation, and resource exploration.

[0003] Chinese patent document CN111268131B discloses a drone inspection device, belonging to the field of equipment inspection technology, including a drone body, support columns, protective curtains, and protective doors: the drone body is equipped with a slide rail, on which a camera is slidably mounted; there are four support columns, which are symmetrically arranged in pairs around the slide rail, with one end of the support column connected to the drone body and the other end connected to a base plate, and the support column is equipped with a vertical sliding groove; there are three protective curtains, which are located between two support columns and can slide along the vertical sliding grooves on the support columns on both sides; there are two protective doors, which are respectively located on two adjacent support columns and are opposite to the lens of the camera, and the two protective doors can move towards each other to close, and the protective doors and protective curtains protect the camera by closing.

[0004] After the drone inspection is completed, staff will return the drone to the hangar for storage and protection. However, during the operation of the aforementioned drone inspection equipment, when the drone is returned to the hangar after the inspection, it will descend to the hangar's apron surface. If one side of the drone's frame touches the ground first, while the other side does not, the drone's center of gravity will shift. This will affect the balance of the aircraft during landing, causing the frame that touches the apron surface first to experience a greater impact force, leading to vibration and bouncing of the aircraft. The strong vibration may affect the drone's storage equipment, resulting in the loss or damage of flight data. Summary of the Invention

[0005] In order to overcome the shortcomings of the prior art, the present invention provides a foldable rotary-wing UAV for field geological exploration, which solves the problem of the above-mentioned vibration and bouncing of the fuselage. Strong vibrations may affect the storage device of the UAV, resulting in the loss or damage of flight data.

[0006] To achieve the above objectives, the technical solution adopted by the present invention is as follows: A folding rotary-wing drone for field geological exploration includes a drone, which has a fuselage with wings installed on all four sides. The fuselage is equipped with a shock-absorbing component, which includes a base installed at the bottom of the fuselage. Support legs are fixed on both sides of the base. A base plate is installed on the upper side of the base and is installed at the bottom of the fuselage. Multiple equidistant lifting shafts are fixed on the top of the base. The top of the multiple lifting shafts is fixed with the same annular plate. An annular cylinder is installed on the outside of the annular plate. The opening end of the annular cylinder is fixed to the top of the base plate. An airbag is fixed on the top of the annular plate.

[0007] Preferably, the plurality of lifting shafts are arranged in a ring on the top of the base, and the base plate is provided with a first limiting hole adapted to the lifting shaft. The lifting shaft and the first limiting hole correspond one-to-one, and the lifting shaft and the corresponding first limiting hole are coaxially arranged, and the lifting shaft is slidably connected inside the corresponding first limiting hole.

[0008] Preferably, the outer wall of the annular cylinder is fixedly connected to an air inlet.

[0009] Preferably, each of the lifting shafts is provided with a return spring on its exterior, the top of each return spring is fixed to the bottom of the base plate, and the bottom of each return spring is fixed to the top of the base.

[0010] Preferably, the machine body is provided with a stabilizing component, which includes a drive shaft disposed in the middle of the base plate, a sleeve disposed on the outside of the drive shaft, and the sleeve is coaxially disposed with the drive shaft, and the outer wall of the drive shaft is attached to the inner wall of the sleeve, the drive shaft can slide up and down along the axial direction of the sleeve, and a positioning hole adapted to the sleeve is provided on the base plate, and the sleeve is coaxially disposed with the positioning hole, and the outer wall of the sleeve is fixed to the inner wall of the positioning hole.

[0011] Preferably, the outer wall of the drive shaft is fixed with a linkage block, and the inner wall of the sleeve is provided with a linkage groove that matches the linkage block, and the linkage block is slidably connected inside the linkage groove.

[0012] Preferably, the linkage groove is spiral-shaped.

[0013] Preferably, two counterweights are symmetrically installed on the surface of the base plate, and the surface of the base plate is provided with slides that are adapted to the counterweights. The counterweights are slidably connected inside the corresponding slides.

[0014] Preferably, an annular disk is fixed to the top of the drive shaft, and a top shaft is fixed to the top of each of the two counterweights. Two arc-shaped grooves are symmetrically opened on the annular disk, and the top shaft is slidably connected inside the arc-shaped grooves.

[0015] Preferably, a support shaft is installed at the mounting end of the wing, a first mounting hole adapted to the support shaft is provided on the fuselage, and a second mounting hole adapted to the support shaft is provided at the mounting end of the support shaft. The support shaft is sequentially inserted into the first mounting hole and the second mounting hole to stabilize the wing.

[0016] The beneficial effects of this invention are as follows: 1. By adopting a folding wing design, and with the precise insertion and connection of the support shaft and the first and second mounting holes, the wings can be quickly folded and unfolded. After folding, the overall space occupied by the drone can be greatly reduced, making it easier for staff to carry and transport in rugged terrain in the field. It also avoids the wings from becoming loose due to airflow disturbances and fuselage vibration during flight, ensuring the flight stability of high-altitude field survey operations. This solves the problems of cumbersome wing fixing and inconvenient storage of traditional drones.

[0017] 2. The fuselage is shock-absorbing through the combined action of the return spring, the sealed gas in the annular cylinder, and the airbag: The return spring can directly buffer the vertical impact force when the fuselage lands, reducing the transmission of vibration to the interior of the fuselage; the annular cylinder and the annular plate form a sealed cavity. When landing, the annular plate moves up and compresses the internal gas, using the gas damping effect to consume the vibration energy. At the same time, the airbag is squeezed to generate flexible buffer, further absorbing residual vibration. This multi-layered approach offsets the impact vibration when the UAV lands on the tarmac, preventing damage or displacement of the internal precision components and the geological exploration instruments (such as mapping cameras and sensors) due to bumps and vibrations.

[0018] 3. When the support feet touch the ground and drive the base to move upward, the linkage block slides along the spiral linkage groove, driving the drive shaft to rotate. This, in turn, drives the top shaft to slide through the arc groove on the annular disc, causing the two counterweight blocks to slide synchronously in opposite directions to directly above the support feet. This increases the load on the support point in real time, reducing the risk of tipping or shifting due to the center of gravity shift when the drone lands, and significantly improving the drone's ability to maintain a horizontal position after landing on the tarmac. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the structure of the present invention; Figure 2 This is a schematic diagram of the UAV structure of the present invention; Figure 3 This is a schematic diagram of the structure of the shock absorption component of the present invention; Figure 4 This is a schematic diagram of the structure of the stabilizing component of the present invention; Figure 5 This is a schematic diagram of the three-dimensional cross-section of the annular cylinder of the present invention; Figure 6 This is a schematic diagram of the three-dimensional cross-section of the sleeve of the present invention.

[0020] In the picture: 10. Unmanned Aerial Vehicle (UAV); 11. Fuselage; 12. Wing; 13. Support Shaft; 14. First Mounting Hole; 15. Second Mounting Hole; 20. Shock absorption assembly; 21. Base; 22. Support leg; 23. Base plate; 24. Lifting shaft; 25. Limiting hole; 26. Annular plate; 27. Annular cylinder; 28. Air inlet; 29. ​​Airbag; 210. Return spring; 211. Suction cup; 30. Stabilizing component; 31. Drive shaft; 32. Sleeve; 34. Positioning hole; 35. Linkage block; 36. Linkage groove; 37. Counterweight block; 38. Slide rail; 39. Annular disc; 310. Top shaft; 311. Arc groove. Detailed Implementation

[0021] The embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Those skilled in the art should understand that these embodiments are merely illustrative of the technical principles of the present invention and are not intended to limit the scope of protection of the present invention.

[0022] Reference Appendix Figures 1-6 As shown, a folding rotary-wing UAV for field geological exploration includes a UAV 10. The UAV 10 includes a fuselage 11, with wings 12 installed on all four sides of the fuselage 11. A support shaft 13 is installed at the mounting end of the wing 12. A first mounting hole 14 adapted to the support shaft 13 is opened on the fuselage 11, and a second mounting hole 15 adapted to the support shaft 13 is opened at the mounting end of the support shaft 13. The support shaft 13 is sequentially inserted into the first mounting hole 14 and the second mounting hole 15, thereby stabilizing the wing 12.

[0023] The fuselage 11 is equipped with a shock-absorbing component 20 to reduce the vibration generated when the drone 10 lands on the ground.

[0024] The shock absorption assembly 20 includes a base 21 installed at the bottom of the fuselage 11. Support legs 22 are fixed to both sides of the base 21 to support the fuselage 11 and maintain its stability. A base plate 23 is provided on the upper side of the base 21 and is installed at the bottom of the fuselage 11. Multiple equidistant lifting shafts 24 are fixed to the top of the base 21, arranged in a ring on the top of the base 21. The base plate 23 has first limiting holes 25 that are compatible with the lifting shafts 24, and each lifting shaft 24 corresponds to one of the first limiting holes 25. The lifting shafts 24 and their corresponding first limiting holes 25 are coaxially arranged and slidably connected inside the corresponding first limiting holes 25. When the support legs 22 move the base 21 upwards, the lifting shafts 24 move upwards along the axial direction of the first limiting holes 25 to limit the position of the base 21. Suction cups 211 are installed at the bottom of the support legs 22, allowing them to adhere to the surface of the apron.

[0025] The top of multiple lifting shafts 24 is fixed with the same annular plate 26. An annular cylinder 27 is provided on the outside of the annular plate 26. The cylinder opening end of the annular cylinder 27 is fixed to the top of the base plate 23. An air inlet 28 is fixedly connected to the outer wall of the annular cylinder 27. An air bag 29 is fixed to the top of the annular plate 26.

[0026] It should be noted that since the opening end of the annular cylinder 27 is fixedly connected to the top of the base plate 23, the inside of the annular cylinder 27 is sealed, while the outer arc surface of the annular plate 26 abuts against the inner wall of the annular cylinder 27, and the air inlet 28 is located at the top of the annular cylinder 27, when the base 21 moves upward, the base 21 drives the annular plate 26 to move upward inside the annular cylinder 27 through the lifting shaft 24. At this time, the annular plate 26 will compress the gas above it, and the airbag 29 will abut against the inner top wall of the annular cylinder 27 due to the movement of the annular plate 26. By compressing the gas inside the annular cylinder 27 and the airbag 29, the vibration generated when the fuselage 11 lands is reduced.

[0027] Each lifting shaft 24 is equipped with a return spring 210 on its exterior. The top of each return spring 210 is fixed to the bottom of the base plate 23, and the bottom of each return spring 210 is fixed to the top of the base 21, so as to reduce the vibration caused by the reaction force generated when the machine body 11 lands.

[0028] A stabilizing component 30 is installed on the fuselage 11 to improve the stability of the fuselage 11 when it lands.

[0029] The stabilizing assembly 30 includes a drive shaft 31 disposed in the middle of the base plate 23. A sleeve 32 is disposed on the outside of the drive shaft 31, and the sleeve 32 is coaxially disposed with the drive shaft 31. The outer wall of the drive shaft 31 is attached to the inner wall of the sleeve 32. The drive shaft 31 can slide up and down along the axial direction of the sleeve 32. A positioning hole 34 adapted to the sleeve 32 is provided on the base plate 23, and the sleeve 32 is coaxially disposed with the positioning hole 34. The outer wall of the sleeve 32 is fixed in the positioning hole 34. On the inner wall of the drive shaft 31, a linkage block 35 is fixed to the outer wall. The inner wall of the sleeve 32 is provided with a linkage groove 36 that matches the linkage block 35. The linkage block 35 is slidably connected inside the linkage groove 36. Two counterweight blocks 37 are symmetrically installed on the surface of the base plate 23. The surface of the base plate 23 is provided with a slide rail 38 that matches the counterweight block 37. The counterweight block 37 is slidably connected inside the corresponding slide rail 38.

[0030] An annular disk 39 is fixed to the top of the drive shaft 31, and a top shaft 310 is fixed to the top of each of the two counterweights 37. Two arc-shaped grooves 311 are symmetrically opened on the annular disk 39, and the top shaft 310 is slidably connected inside the arc-shaped grooves 311.

[0031] It should be noted that since the linkage groove 36 is spiral and the arc groove 311 is arc-shaped, when the support leg 22 abuts against the ground and drives the base 21 to move upward, the linkage block 35 slides along the extension trajectory of the linkage groove 36. The linkage block 35 drives the drive shaft 31 to rotate inside the sleeve 32, and the top shaft 310 slides along the extension trajectory of the arc groove 311. At this time, the counterweight block 37 slides along the extension trajectory of the slide rail 38. The two counterweight blocks 37 slide synchronously in opposite directions toward the edge of the base plate 23 to apply weight to the support leg 22 and improve the stability of the body 11.

[0032] During use, the usage status of the drone 10 is controlled by the control terminal. When the drone 10 is finished using, as it lands on the apron, the bottom of the support leg 22 will abut against the surface of the apron. At this time, due to the weight of the fuselage 11, the fuselage 11 will move downward, while the support leg 22 will drive the base 21 to move upward. The base plate 23 will compress the return spring 210 to reduce shock. At the same time, the lifting shaft 24 will move upward inside the first limit hole 25, and the lifting shaft 24 will drive the annular plate 26 to move upward inside the annular cylinder 27 to compress the gas and airbag 29 inside the annular cylinder 27, thereby reducing the vibration generated when the fuselage 11 lands.

[0033] As the base plate 23 moves upward, the drive shaft 31 moves upward inside the sleeve 32, while the linkage block 35 slides along the extension trajectory of the linkage groove 36. The drive shaft 31 drives the annular disk 39 to rotate, and the top shaft 310 slides along the arc groove 311 from one end near the axis to the other end. At this time, the top shaft 310 drives the counterweight block 37 to slide directly above the support leg 22 to add weight to the support leg 22, thereby improving the stability of the fuselage 11 when it lands.

[0034] The technical solution of the present invention has been described above with reference to the preferred embodiments shown in the accompanying drawings. However, it will be readily understood by those skilled in the art that the scope of protection of the present invention is obviously not limited to these specific embodiments. Without departing from the principles of the present invention, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after such changes or substitutions will all fall within the scope of protection of the present invention.

Claims

1. A folding rotary-wing unmanned aerial vehicle (UAV) specifically designed for field geological exploration, characterized in that: The drone (10) includes a fuselage (11), and wings (12) are installed around the fuselage (11). A shock-absorbing component (20) is provided on the fuselage (11). The shock-absorbing component (20) includes a base (21) installed at the bottom of the fuselage (11). Support legs (22) are fixed on both sides of the base (21). A base plate (23) is provided on the upper side of the base (21). The base plate (23) is installed at the bottom of the fuselage (11). Multiple equidistant lifting shafts (24) are fixed on the top of the base (21). The same annular plate (26) is fixed on the top of the multiple lifting shafts (24). An annular cylinder (27) is provided on the outside of the annular plate (26). The opening end of the annular cylinder (27) is fixed on the top of the base plate (23). An airbag (29) is fixed on the top of the annular plate (26).

2. The folding rotary-wing UAV for field geological exploration according to claim 1, characterized in that, Multiple lifting shafts (24) are arranged in a ring on the top of the base (21). The base plate (23) is provided with a first limiting hole (25) that is compatible with the lifting shaft (24). The lifting shaft (24) and the first limiting hole (25) correspond one-to-one. The lifting shaft (24) and the corresponding first limiting hole (25) are coaxially arranged. The lifting shaft (24) is slidably connected inside the corresponding first limiting hole (25).

3. The folding rotary-wing UAV for field geological exploration according to claim 2, characterized in that, An air inlet (28) is fixedly connected to the outer wall of the annular cylinder (27).

4. The folding rotary-wing UAV for field geological exploration according to claim 3, characterized in that, Each of the lifting shafts (24) is provided with a return spring (210) on its exterior. The top of each return spring (210) is fixed to the bottom of the base plate (23), and the bottom of each return spring (210) is fixed to the top of the base (21).

5. The folding rotary-wing UAV for field geological exploration according to claim 4, characterized in that, The body (11) is provided with a stabilizing component (30). The stabilizing component (30) includes a drive shaft (31) located in the middle of the base plate (23). A sleeve (32) is provided on the outside of the drive shaft (31). The sleeve (32) is coaxially arranged with the drive shaft (31). The outer wall of the drive shaft (31) is attached to the inner wall of the sleeve (32). The drive shaft (31) can slide up and down along the axial direction of the sleeve (32). A positioning hole (34) adapted to the sleeve (32) is provided on the base plate (23). The sleeve (32) is coaxially arranged with the positioning hole (34). The outer wall of the sleeve (32) is fixed on the inner wall of the positioning hole (34).

6. The folding rotary-wing UAV for field geological exploration according to claim 5, characterized in that, The outer wall of the drive shaft (31) is fixed with a linkage block (35), and the inner wall of the sleeve (32) is provided with a linkage groove (36) that is compatible with the linkage block (35), and the linkage block (35) is slidably connected inside the linkage groove (36).

7. The folding rotary-wing UAV for field geological exploration according to claim 6, characterized in that, The linkage groove (36) is spiral-shaped.

8. The folding rotary-wing UAV for field geological exploration according to claim 6, characterized in that, Two counterweights (37) are symmetrically installed on the surface of the base plate (23). The surface of the base plate (23) is provided with a slide (38) that matches the counterweights (37). The counterweights (37) are slidably connected inside the corresponding slide (38).

9. The folding rotary-wing UAV for field geological exploration according to claim 8, characterized in that, The top of the drive shaft (31) is fixed with an annular disk (39), and the top of the two counterweights (37) is fixed with a top shaft (310). Two arc-shaped grooves (311) are symmetrically opened on the annular disk (39), and the top shaft (310) is slidably connected inside the arc-shaped grooves (311).

10. The folding rotary-wing UAV for field geological exploration according to claim 1, characterized in that, The wing (12) is equipped with a support shaft (13) at its mounting end. The fuselage (11) has a first mounting hole (14) that matches the support shaft (13). The mounting end of the support shaft (13) has a second mounting hole (15) that matches the support shaft (13). The support shaft (13) is inserted into the first mounting hole (14) and the second mounting hole (15) in sequence to stabilize the wing (12).

Images