An unmanned aerial vehicle flight protection device for geological surveying

Abstract

The present application belongs to the technical field of aircraft protection device, and particularly relates to a flight protection device for unmanned aerial vehicle used for geological survey, which comprises a mounting mechanism, a support and a propeller guard frame. The flight protection device can protect the propeller, thus ensuring the flight safety of the unmanned aerial vehicle to a certain extent, especially when the unmanned aerial vehicle performs a cliff survey task, the propeller can be prevented from colliding with the cliff wall, so that the cliff survey task can be smoothly performed. In addition, when the unmanned aerial vehicle falls from the air due to failure, each support can support the fuselage of the unmanned aerial vehicle and support the propeller motor when the support hits hard geology such as rock, thus forming support at both ends of the connecting arm at the same time, inhibiting the bending deformation of the connecting arm, and avoiding the fracture of the connecting arm after the unmanned aerial vehicle falls and hits hard geology to a certain extent, thus improving the anti-collision capability of the unmanned aerial vehicle and prolonging its service life.

Description

Technical Field

[0001] This invention belongs to the technical field of aircraft protection devices, specifically relating to a flight protection device for unmanned aerial vehicles (UAVs) used for geological surveys. Background Technology

[0002] Drones are commonly used tools in geological surveying activities. For complex geological conditions, drones are often used in conjunction with geological survey cameras for remote control surveying operations. This can significantly reduce the workload of surveyors and improve surveying efficiency. While currently available drones for geological surveying can output relatively good survey data, they still have certain shortcomings in use, such as those mentioned in the instruction manual. Figure 1 As shown, drones used for geological surveys on the market mainly consist of a fuselage 11, a propeller motor 12, a connecting arm 13, a propeller 14, a landing gear 15, and a geological survey camera 16. When such drones are conducting rock and landform surveys, if the drone malfunctions and falls from the air, it will directly impact hard rocks. The propeller motor 12 is suspended at the end of the connecting arm 13 away from the fuselage 11, and the propeller motor 12 has no other protective measures besides the support of the connecting arm 13. Thus, after the landing gear 15 falls and impacts hard geological formations such as rocks, the falling inertia of the propeller motor 12 can easily cause the connecting arm 13 to break and be damaged. Therefore, to address the above problems, we propose a flight protection device for drones used in geological surveys. Summary of the Invention

[0003] To overcome the problems existing in related technologies, this invention discloses a flight protection device for unmanned aerial vehicles (UAVs) used in geological surveys.

[0004] To achieve the above objectives, one technical solution adopted by the present invention is:

[0005] A flight protection device for unmanned aerial vehicles (UAVs) used in geological surveying includes:

[0006] The mounting mechanism is installed on the fuselage of the drone;

[0007] The support component has one end mounted on the mounting mechanism. The number of the support components is the same as the number of propeller motors of the UAV, and their positions correspond one-to-one.

[0008] The number of propeller guards is the same as the number of propeller motors of the drone, and their positions correspond one-to-one. The propeller guards are located between the propeller motors and the support members. Each support member is connected to the drone's fuselage and the corresponding connecting arm, propeller motor, and propeller guard to form a triangular structure.

[0009] Furthermore, the propeller guard is detachably connected between the propeller motor and the support.

[0010] Furthermore, the propeller guard includes a frame and a middle rod, the frame having a first sliding groove extending vertically through it, and the middle rod being slidably fitted into the first sliding groove;

[0011] The support includes a support tube, a first piston is slidably and sealingly connected to the inner wall of the support tube corresponding to one end of the first groove, and a second piston is slidably and sealingly connected to the inner wall of the support tube corresponding to one end of the mounting mechanism. The support tube is provided with a first elastic element for pushing the second piston away from the first piston, and the second piston cannot extend out of the support tube.

[0012] The support tube is filled with a liquid medium located between the first piston and the second piston;

[0013] The mounting mechanism can control the second piston to move closer to or further away from the first elastic element.

[0014] Furthermore, the support tube includes a tube body and a connector. The two ends of the tube body are bent upward to form a lower vertical section and an upper vertical section, respectively. The first piston is located in the lower vertical section. The connector is located at the upper end of the upper vertical section. A second sliding groove communicating with the tube body is opened on the side of the connector. The second piston and the first elastic member are both located in the second sliding groove. The second piston cannot extend out of the second sliding groove.

[0015] Furthermore, the support member is detachably connected to the mounting mechanism.

[0016] Furthermore, the mounting mechanism includes a mounting shell, an adjusting member disposed in the middle of the mounting shell, and a plug-in shell disposed inside the mounting shell for the plug-in member to be inserted into. The number of plug-in shells is consistent with the number of propeller motors of the UAV, and their positions correspond one-to-one. A third sliding groove with internal and external communication is opened at the end of the plug-in shell near the adjusting member.

[0017] The mounting mechanism further includes an adjusting rod slidably fitted in the third groove and a second elastic member disposed on the plug-in housing for pushing the adjusting rod toward the adjusting member, the adjusting member being able to control the axial movement of the adjusting rod.

[0018] Furthermore, the adjusting component is longitudinally slidably assembled inside the mounting housing. The side of the adjusting component is provided with a first cylindrical surface, a second cylindrical surface, and a third cylindrical surface from bottom to top. The diameter of the first cylindrical surface is larger than the diameter of the second cylindrical surface, which is larger than the diameter of the third cylindrical surface. The first cylindrical surface and the second cylindrical surface are connected by a first guide slope, and the second cylindrical surface and the third cylindrical surface are connected by a second guide slope.

[0019] Furthermore, the end of the adjusting rod near the adjusting member is a spherical surface, and the first cylindrical surface is provided with a first spherical groove corresponding to the position of each adjusting rod, the depth of the first spherical groove being less than the diameter of the adjusting rod.

[0020] Furthermore, a second spherical groove is provided on the second cylindrical surface corresponding to the position of each adjusting rod, and the depth of the second spherical groove is less than the diameter of the adjusting rod.

[0021] Furthermore, a third spherical groove is provided on the third cylindrical surface corresponding to the position of each adjusting rod, and the depth of the third spherical groove is less than the diameter of the adjusting rod.

[0022] This invention discloses a flight protection device for unmanned aerial vehicles (UAVs) used in geological surveys. This device can protect the propeller, thus ensuring the flight safety of the UAV to a certain extent. In particular, it can prevent the propeller from colliding with the cliff face when the UAV is performing a cliff survey, allowing the survey to be carried out smoothly. In addition, when the UAV crashes from the air due to a malfunction and the supporting components hit hard geological surfaces such as rocks, the supporting components can support both the UAV fuselage and the propeller motor. This provides support at both ends of the connecting arm, inhibiting bending deformation of the connecting arm and preventing the connecting arm from breaking after the UAV crashes into hard geological surfaces. This improves the UAV's collision resistance and extends its service life. Attached Figure Description

[0023] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments of this application and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0024] Figure 1 This is a schematic diagram of the structure of a drone in the prior art;

[0025] Figure 2 This is a schematic diagram of a structure according to an embodiment of the present invention;

[0026] Figure 3 This is a schematic diagram of an embodiment of the present invention without the propeller guard installed;

[0027] Figure 4 This is a schematic diagram of an embodiment of the present invention without the support member and propeller guard installed;

[0028] Figure 5 for Figure 4 Enlarged structural diagram at point A;

[0029] Figure 6 This is a schematic cross-sectional view of a first embodiment of the present invention;

[0030] Figure 7 for Figure 6 Enlarged structural diagram at point B;

[0031] Figure 8 This is a schematic diagram of a second cross-sectional structure according to an embodiment of the present invention.

[0032] The meanings of the labels in the attached diagram are as follows:

[0033] 11. Fuselage; 12. Propeller motor; 121. Intermediate rod slot; 13. Connecting arm; 14. Propeller; 15. Tripod; 16. Geological survey camera; 2. Mounting mechanism; 21. Mounting shell; 211. Rectangular rod; 2111. Third limiting ring; 22. Adjusting component; 220. Third slide groove; 221. First cylindrical surface; 2211. First spherical groove; 2221. Second cylindrical surface; 2222. Second spherical groove; 2221. Third cylindrical surface; 223. Third spherical groove; 2231. First guide slope; 224. Second guide slope. Surface 225, rectangular groove 226, plug-in shell 23, adjusting rod 24, second limiting ring 241, second elastic element 25, support element 3, tube body 311, lower vertical section 3111, upper vertical section 3112, plug-in element 312, second sliding groove 3121, first limiting ring 3122, first piston 32, second piston 33, first elastic element 34, propeller guard frame 4, frame body 41, first sliding groove 411, regular octagonal plug groove 412, middle rod 42, regular octagonal plug 421. Detailed Implementation

[0034] The invention will now be further described with reference to the accompanying drawings.

[0035] Reference Figure 2-8 As shown, the UAV flight protection device for geological surveying in this embodiment includes an installation mechanism 2, support members 3, and propeller guards 4. This UAV flight protection device needs to be used in conjunction with a UAV. In this embodiment, the UAV has four propeller motors 12 and four connecting arms 13, which are arranged in an "X" shape. In this embodiment, the installation mechanism 2 is installed on the lower part of the UAV fuselage 11. The inner end of each of the four support members 3 is connected to the installation mechanism 2, and the outer end of each of the four support members 3 is connected to the lower end of the corresponding four propeller motors 12 through the four propeller guards 4. The lower end of each of the four support members 3 is at the bottom of the entire assembly formed by the UAV flight protection device and the UAV. That is, when the UAV is placed on the ground, the four support members 3 are in contact with the ground. Thus, the four support members 3, the UAV fuselage 11, the corresponding connecting arms 13, the propeller motors 12, and the propeller guards 4 form a triangular structure, and the four support members 3 can act as tripods to support the entire UAV on the ground.

[0036] After the drone is equipped with this flight protection device, each propeller guard 4 will surround the outside of the propeller 14 to protect it. This can ensure the drone's flight safety to a certain extent, especially when the drone is performing cliff surveying tasks, preventing the propeller 14 from colliding with the cliff face and ensuring the smooth execution of the survey. In addition, when the drone falls from the air due to a malfunction and the support components 3 impact hard geological surfaces such as rocks, the support components 3 can support both the drone's fuselage 11 and the propeller motor 12. This can simultaneously provide support at both ends of the connecting arm 13, inhibiting bending deformation of the connecting arm 13 and preventing it from breaking after the drone crashes into hard geological surfaces. This improves the drone's collision resistance and extends its service life.

[0037] Considering that the propeller guard 4 and the support 3 are located on the outermost side of the UAV and are easily damaged by impact, they need to be replaced after damage. In order to facilitate the replacement of the propeller guard 4 and the support 3, in this embodiment, the propeller guard 4 is detachably connected between the propeller motor 12 and the support 3, and the support 3 is detachably connected to the mounting mechanism 2. This detachable connection method is a quick-release design to quickly realize disassembly and assembly.

[0038] Specifically, the propeller guard 4 includes a frame 41 and a middle rod 42. The frame 41 has a first sliding groove 411 that runs vertically through the frame, and the middle rod 42 is slidably fitted into the first sliding groove 411. Correspondingly, a middle rod slot 121 for inserting the middle rod 42 is pre-set at the lower end of the UAV's propeller motor 12.

[0039] Specifically, the support member 3 includes a support tube, which comprises a tube body 311 and a connector 312. The two ends of the tube body 311 are bent upwards to form a lower vertical section 3111 and an upper vertical section 3112, respectively. The connector 312 is fixed to the upper end of the upper vertical section 3112. A second groove 3121 communicating with the tube body 311 is formed on the side of the connector 312. A second piston 33 is slidably connected within the second groove 3121, and a first piston 32 is slidably connected within the lower vertical section 3111. A first elastic element 34 for pushing the second piston 33 away from the first piston 32 is fitted within the second groove 3121. In this embodiment, the first elastic element 34 is a helical spring. Furthermore, the support tube is filled with a liquid medium located between the first piston 32 and the second piston 33. In this embodiment, the liquid medium is hydraulic oil. To restrict the second piston 33 from extending beyond the second groove 3121, a first limiting ring 3122 is fixedly provided at the opening of the second groove 3121. When the support member 3 is not installed together with the mounting mechanism 2, the second piston 33 will be pushed outward by the first elastic member 34 to abut against the first limiting ring 3122. In this state, the upper end of the first piston 32 will be flush with the upper end of the lower vertical section 3111 under the negative pressure of the hydraulic oil.

[0040] Specifically, the mounting mechanism 2 includes a mounting shell 21 fixedly attached to the lower end of the fuselage 11. In this embodiment, a mounting shell assembly slot for accommodating the mounting shell 21 is provided at the lower end of the fuselage 11 of the UAV. The mounting shell 21 is fixed in the mounting shell assembly slot by multiple screws. Four plug-in shells 23 for plugging into the plug-in parts 312 are fixedly attached inside the mounting shell 21. The positions of the four plug-in shells 23 correspond to the positions of the four connecting arms 13. A third sliding groove 220 with internal and external communication is provided at one end of the plug-in shell 23 facing the middle of the mounting shell 21. An adjusting rod 24 is slidably mounted in the third sliding groove 220. In addition, a second elastic element 25 for pushing the adjusting rod 24 toward the middle of the mounting shell 21 is also provided on the plug-in shell 23. In this embodiment, the second elastic element 25 is a helical spring. A second limiting ring 241 is also provided on the side of the adjusting rod 24. The second elastic element 25 is sleeved on the outside of the adjusting rod 24, and its two ends abut against the second limiting ring 241 and the plug-in shell 23, respectively.

[0041] Specifically, the mounting mechanism 2 also includes an adjusting member 22 that is longitudinally slidably assembled in the middle of the inner side of the mounting shell 21. In order to achieve longitudinal sliding connection, in this embodiment, the adjusting member 22 is a hollow structure with an open bottom. The top of the adjusting member 22 is provided with a rectangular groove 226 that runs through the top and bottom. A longitudinally arranged rectangular rod 211 is fixedly connected to the middle of the inner side of the mounting shell 21. The adjusting member 22 is sleeved on the outside of the rectangular rod 211 through the rectangular groove 226. In addition, a third limiting ring 2111 for limiting the adjusting member 22 from completely disengaging from the rectangular rod 211 is fixedly connected to the lower end of the rectangular rod 211 by screws. The adjusting member 22 has a first cylindrical surface 221, a second cylindrical surface 222, and a third cylindrical surface 223 arranged sequentially from bottom to top on its side. The diameter of the first cylindrical surface 221 is larger than the diameter of the second cylindrical surface 222, which is larger than the diameter of the third cylindrical surface 223. The first cylindrical surface 221 and the second cylindrical surface 222 are connected by a first guide slope 224, and the second cylindrical surface 222 and the third cylindrical surface 223 are connected by a second guide slope 225.

[0042] When the support member 3 is not installed together with the mounting mechanism 2, each of the second elastic members 25 will push the corresponding adjusting rod 24 toward one side of the adjusting member 22, so that each adjusting rod 24 abuts against the outside of the adjusting member 22.

[0043] When assembling the drone flight protection device with the drone, the drone is placed in an inverted position. Then, the mounting mechanism 2 is installed on the bottom of the drone's fuselage 11. At this time, each adjusting rod 24 must be kept in contact with the third cylindrical surface 223, that is, the end of the adjusting rod 24 away from the adjusting member 22 is retracted into the third sliding groove 220. This step prepares for the insertion of the connector 312. After that, the middle rod 42 of each propeller guard frame 4 is inserted into the corresponding middle rod slot 121. Then, the frame 41 is fitted onto the outside of the intermediate rod 42 through the first slide groove 411, and the frame 41 is kept in contact with the propeller motor 12. Then, each support member 3 is inserted into each plug shell 23 through the plug-in member 312. After insertion, the plug shell 23 will restrict the lateral movement and rotation of the plug-in member 312, and the second slide groove 3121 will be aligned with the third slide groove 220. In addition, the upper end of the lower vertical section 3111 will abut against the frame 41, and the first piston 32 will be axially aligned with the first slide groove 411. After the insertion of each support member 3 is completed, the adjusting member 22 is pushed downwards. During the downward movement of the adjusting member 22, the second guide slope 225 abuts against the ends of each adjusting rod 24, guiding and pushing each adjusting rod 24 outwards. When the adjusting member 22 moves downwards and abuts against the adjusting rod 24 through the second cylindrical surface 222, the end of each adjusting rod 24 away from the adjusting member 22 will be in the second sliding groove 3121 but not in contact with the second piston 33. In this state, the adjusting rod 24 will restrict the longitudinal movement of the insertion member 312, and the insertion member 312 will be locked in the insertion shell 23. Each support member 3 will then be fixed together with the mounting mechanism 2. It is worth mentioning that in this state, each first piston 32 does not extend out of the tube body 311. As the adjusting member 22 continues to be pushed downwards, the first guide slope 224 will abut against the ends of each adjusting rod 24. In this way, the first guide slope 224 will guide and push each adjusting rod 24, causing each adjusting rod 24 to move outwards along the axis. When the adjusting member 22 moves downwards and abuts against the adjusting rod 24 through the first cylindrical surface 221, the end of each adjusting rod 24 away from the adjusting member 22 will abut against each second piston 33 and push it a certain distance towards the first piston 32. This causes each second piston 33 to push the corresponding first piston 32 part out of the tube body 311 in conjunction with the hydraulic oil. The first piston 32 that extends out of the tube body 311 will insert into the first slide groove 411. In this state, the first piston 32 will prevent the intermediate rod 42 from disengaging from the intermediate rod slot 121. In this way, the frame 41 is locked between the propeller motor 12 and the tube body 311. The propeller guard frame 4 is then fixed together with the propeller motor 12 and the support member 3. The drone flight protection device and the drone are now assembled.

[0044] In this embodiment, preferably, the upper end of the intermediate rod 42 has a regular octagonal plug 421, and the lower end of the inner side of the frame 41 has a regular octagonal plug slot 412 to accommodate the regular octagonal plug 421. Correspondingly, the cross-section of the intermediate rod slot 121 is also a regular octagon that matches the regular octagonal plug 421. Thus, after the propeller guard 4 is installed between the propeller motor 12 and the support member 3, the lower part of the regular octagonal plug 421 will be located in the regular octagonal plug slot 412, and the regular octagonal plug 421 will be inserted into the intermediate rod slot 121, thereby restricting the rotation of the propeller guard 4 relative to the propeller motor 12 or the support member 3. Furthermore, preferably, the distance between the lower end of the intermediate rod 42 and the upper end of the regular octagonal plug 421 is equal to the distance between the upper end of the regular octagonal plug slot 412 and the lower end of the first slide groove 411. In this way, after the first piston 32 is inserted into the first slide groove 411, the regular octagonal plug 421 will be inserted into the intermediate rod slot 121.

[0045] It should be noted that the longitudinal position between the adjusting member 22 and the mounting shell 21 can be kept fixed by the abutment action of each adjusting rod 24. That is, when the adjusting rod 24 and the adjusting member 22 are kept in contact by the second elastic member 25, the axial movement of the adjusting member 22 relative to the mounting shell 21 is restricted by the friction between the adjusting member 22 and the adjusting rod 24. When the user pushes or pulls the adjusting member 22, it can be driven to move axially. It is worth mentioning that this embodiment adopts another more stable structural form. Specifically, the end of the adjusting rod 24 near the adjusting member 22 is a spherical surface. The first cylindrical surface 221 is provided with a first spherical groove 2211 corresponding to the position of each adjusting rod 24, the second cylindrical surface 222 is provided with a second spherical groove 2221 corresponding to the position of each adjusting rod 24, and the third cylindrical surface 223 is provided with a third spherical groove 2231 corresponding to the position of each adjusting rod 24. The depth of the first spherical groove 2211, the second spherical groove 2221, and the third spherical groove 2231 is all less than the diameter of the adjusting rod 24. In this way, each adjusting rod 24 can be inserted into the corresponding spherical groove for fixation. This insertion and fixation provides more stable support, so the adjusting member 22 is not easily allowed to slide longitudinally. When it is necessary to move the adjusting member 22 longitudinally, simply push or pull the adjusting member 22 to complete the adjustment.

[0046] When it is necessary to disassemble the propeller guard 4, the adjusting member 22 is pulled axially away from the fuselage 11. When the adjusting member 22 abuts against each adjusting rod 24 through the second cylindrical surface 222, the end of each adjusting rod 24 away from the adjusting member 22 will retract and reset under the rebound action of each second elastic member 25 until it is no longer in contact with the second piston 33. This allows each second piston 33 to reset under the elastic force of the first elastic member 34 until it remains in contact with the first limiting ring 3122. The first piston 32 is then reset under the negative pressure of the hydraulic oil. When the upper end is aligned with the upper end of the lower vertical section 3111, the intermediate rods 42 are no longer restricted from retracting from the intermediate rod slots 121. The drone can then be positioned upright, allowing the intermediate rods 42 to abut against the upper end of the first piston 32 under gravity, thus disengaging the octagonal plugs 421 from the intermediate rod slots 121. At this point, the propeller guards 4 are no longer fixed to the propeller motor 12 and the support member 3, allowing them to be laterally moved and removed from the propeller motor 12 and the support member 3. This detachable connection method allows for quick assembly and disassembly of the propeller guards 4, facilitating their replacement. It is worth mentioning that after the propeller guards 4 are removed, the support 3 can still be fixed to the mounting mechanism 2 because the adjusting rod 24 can abut against the second cylindrical surface 222 of the adjusting member 22. In this way, the UAV can fly without the propeller guards 4 depending on the flight endurance requirements or the survey environment. This can reduce the flight weight of the UAV, reduce the flight power, and thus extend the flight time of the UAV.

[0047] When it is necessary to disassemble the support member 3, the adjusting member 22 is pulled axially away from the body 11. When the adjusting member 22 abuts against each adjusting rod 24 through the third cylindrical surface 223, the end of each adjusting rod 24 away from the adjusting member 22 will retract into the third sliding groove 220 under the rebound action of each second elastic member 25. In this way, each plug-in member 312 is unlocked from each plug-in shell 23, and each support member 3 can be directly removed from the mounting mechanism 2. It can be seen that this detachable connection method allows for quick disassembly and assembly of each support member 3, so as to facilitate the replacement of the support member 3. It is worth mentioning that after the propeller guards 4 are removed, the support 3 can still be fixed to the mounting mechanism 2 because the adjusting rod 24 can abut against the third cylindrical surface 223 of the adjusting member 22. When the adjusting rod 24 abuts against the third cylindrical surface 223 of the adjusting member 22, the adjusting member 22 will be in the state of extending out of the mounting shell 21, and the lower end of the adjusting member 22 will be lower than the lower end of the geological survey camera 16. In this way, the entire drone can be supported on the ground as a temporary support by the adjusting member 22. In addition, it can also be used as a grip for handheld take-off and handheld landing. Compared with holding the fuselage 11 directly for handheld take-off and landing, it can greatly improve safety. Similarly, eliminating the support 3 for flight can further reduce the flight weight of the drone, thus providing a longer flight time.

[0048] It should be emphasized that when the drone makes a hard landing after the support component 3 is installed, the adjusting component 22 will descend a certain height due to inertia after the support component 3 touches the ground, depending on the speed of the hard landing. It may even descend from the current cylindrical surface to the next higher or even two higher cylindrical surfaces. For example, it may descend from the first cylindrical surface 221 where it abuts against the adjusting rod 24 to the third cylindrical surface 223 where it abuts against the adjusting rod 24. This provides a certain degree of force relief, thus offering some protection. Furthermore, the user can observe the descent height of the adjusting component 22 after the drone lands to determine the severity of the hard landing, serving as a warning. It should be noted that the specific descent force of the adjusting component 22 can be adjusted by changing the coefficient of friction between the adjusting rod 24 and the adjusting component 22, for example, by changing the surface material or altering the elastic strength of the second elastic component 25.

[0049] The above embodiments are merely illustrative of the principles and effects of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in the present invention should still be covered by the claims of the present invention.

Claims

1. A flight protection device for unmanned aerial vehicles (UAVs) used in geological surveying, characterized in that, include: The mounting mechanism is installed on the fuselage of the drone; The support component has one end mounted on the mounting mechanism. The number of the support components is the same as the number of propeller motors of the UAV, and their positions correspond one-to-one. The number of propeller guards is the same as the number of propeller motors of the drone, and their positions correspond one-to-one. The propeller guards are located between the propeller motors and the support components. Each support component is connected to the drone's fuselage and the corresponding connecting arm, propeller motor, and propeller guard to form a triangular structure. The propeller guard is detachably connected between the propeller motor and the support component; The propeller guard includes a frame and a middle rod. The frame has a first sliding groove that runs vertically through it, and the middle rod is slidably fitted into the first sliding groove. The support includes a support tube, a first piston is slidably and sealingly connected to the inner wall of the support tube corresponding to one end of the first groove, and a second piston is slidably and sealingly connected to the inner wall of the support tube corresponding to one end of the mounting mechanism. The support tube is provided with a first elastic element for pushing the second piston away from the first piston, and the second piston cannot extend out of the support tube. The support tube is filled with a liquid medium located between the first piston and the second piston; The mounting mechanism can control the second piston to move closer to or further away from the first elastic element.

2. The UAV flight protection device for geological surveying according to claim 1, characterized in that: The support tube includes a tube body and a connector. The two ends of the tube body are bent upward to form a lower vertical section and an upper vertical section, respectively. The first piston is located in the lower vertical section. The connector is located at the upper end of the upper vertical section. A second sliding groove communicating with the tube body is opened on the side of the connector. The second piston and the first elastic member are both located in the second sliding groove. The second piston cannot extend out of the second sliding groove.

3. The UAV flight protection device for geological surveying according to claim 2, characterized in that: The support member is detachably connected to the mounting mechanism.

4. The UAV flight protection device for geological surveying according to claim 3, characterized in that: The mounting mechanism includes a mounting shell, an adjusting member located in the middle of the mounting shell, and a plug-in shell located inside the mounting shell for the plug-in member to be inserted into. The number of plug-in shells is the same as the number of propeller motors of the UAV, and their positions correspond one-to-one. A third sliding groove with internal and external communication is opened at the end of the plug-in shell near the adjusting member. The mounting mechanism further includes an adjusting rod slidably fitted in the third groove and a second elastic member disposed on the plug-in housing for pushing the adjusting rod toward the adjusting member, the adjusting member being able to control the axial movement of the adjusting rod.

5. The UAV flight protection device for geological surveying according to claim 4, characterized in that: The adjusting component is longitudinally slidably assembled inside the mounting housing. The side of the adjusting component is provided with a first cylindrical surface, a second cylindrical surface and a third cylindrical surface from bottom to top. The diameter of the first cylindrical surface is larger than the diameter of the second cylindrical surface and the diameter of the third cylindrical surface. The first cylindrical surface and the second cylindrical surface are connected by a first guide slope, and the second cylindrical surface and the third cylindrical surface are connected by a second guide slope.

6. The unmanned aerial vehicle (UAV) flight protection device for geological surveying according to claim 5, characterized in that: The end of the adjusting rod near the adjusting component is a spherical surface, and the first cylindrical surface is provided with a first spherical groove corresponding to the position of each adjusting rod. The depth of the first spherical groove is less than the diameter of the adjusting rod.

7. A drone flight protection device for geological surveying according to claim 6, characterized in that: The second cylindrical surface has a second spherical groove corresponding to the position of each adjusting rod, and the depth of the second spherical groove is less than the diameter of the adjusting rod.

8. The UAV flight protection device for geological surveying according to claim 7, characterized in that: The third cylindrical surface has a third spherical groove corresponding to the position of each adjusting rod, and the depth of the third spherical groove is less than the diameter of the adjusting rod.

Images