Unmanned aerial vehicle surveying and mapping device for investigation

Abstract

The invention relates to an unmanned aerial vehicle surveying and mapping device for investigation. An unmanned aerial vehicle is composed of a shell body, a power storage module shell, wings and a supporting mechanism. The storage mechanism is arranged at the top of the machine shell body and comprises a detachably-mounted storage cavity, a parachute is arranged in the storage cavity, a connecting rope at the bottom of the parachute is fixed to the bottom wall of the storage cavity, and a sealing cover plate matched with the wings is arranged at the top of the storage cavity; the two guide mechanisms are respectively arranged in the corresponding supporting mechanisms and are matched with the power storage module shell; an electromagnetic adsorption mechanism is used for maintaining a flight configuration, and the wings are unlocked and automatically folded once power is off; the core innovation lies in that the electricity storage module shell is used as a gravity actuator, and when the electricity storage module shell is separated from the machine shell body and falls down, a thin film of the guide mechanism is forcibly pulled through a pull rope to be unfolded and closed; the structure can effectively push branches aside, eliminate hanging points and guide the unmanned aerial vehicle to penetrate through a tree canopy to slide to the ground, meanwhile, multiple protection is achieved, and the risk of tree hanging and falling damage is remarkably reduced.

Description

A surveying drone mapping device Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) exploration technology and relates to a UAV mapping device for exploration. Background Technology

[0002] Drone mapping technology is widely used in densely vegetated areas such as forests and hills, but the complex and dense canopy also presents serious challenges to drone field operations. Existing multi-rotor drones, for aerodynamic efficiency reasons, generally adopt an "open" structure with outstretched arms and a gimbal mounted underneath. However, this structure poses a significant risk when the drone crashes out of control. When a drone passes through the canopy, its outstretched arms, propellers, and gimbal can easily become entangled in tree branches, acting like a "multi-directional grappling hook," causing the equipment to become firmly trapped tens of meters above the treetop. This "high-altitude hang" not only makes equipment recovery extremely difficult, often requiring significant manpower and resources for logging or climbing, but more dangerously, damaged batteries after a crash can easily short-circuit and cause forest fires, posing a serious safety hazard.

[0003] The key to fundamentally solving this problem lies in enabling the drone to rapidly transform into a smooth, streamlined shape upon impact, minimizing the points of snagging on tree branches. However, existing protective solutions, such as retractable landing gear or folding arms driven by motors, have fatal flaws. When a drone encounters typical incidents like "in-flight power outages" or "flight control failures" that paralyze its electronic systems, these electrically controlled transformation mechanisms immediately fail due to loss of power. During the brief seconds of descent, they cannot execute any pre-set protective actions, leaving the drone to crash into the tree canopy in an easily snagging, "open" state, rendering the protective measures ineffective. Therefore, developing a physical protection mechanism that does not rely on electronic control systems and can be passively triggered in emergency situations has become crucial for improving the survivability of drones in the wild. Summary of the Invention

[0004] In view of this, in order to solve the problem that drones in complex vegetation environments in the wild are prone to getting "hooked" on tree canopies due to their open structure and the failure of protection after power failure, resulting in poor performance, the present invention provides a surveying drone mapping device.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] A surveying and mapping device for unmanned aerial vehicles (UAVs) includes: a UAV, consisting of a fuselage body, a battery storage module housing, wings, and a support mechanism. The wings are four in number and can be folded and located at the four outer corners of the UAV. The battery storage module housing is located at the bottom of the fuselage body. A plug I is embedded at the bottom of the fuselage body, and a plug II that is inserted into the top of the battery storage module housing is embedded in the top of the battery storage module housing. Pull ropes I are fixed at the four bottom corners of the battery storage module housing, and the pull ropes I are fixedly connected to the corresponding wings to support the battery storage module housing.

[0007] The storage mechanism is located on the top of the fuselage body and includes a detachable storage cavity. A parachute is installed inside the storage cavity. The bottom connecting rope of the parachute is fixed to the bottom wall of the storage cavity. A sealing cover plate that cooperates with the wing is provided on the top of the storage cavity.

[0008] Two guiding mechanisms are respectively located in the corresponding support mechanism and cooperate with the battery module housing. When the drone malfunctions, the wings automatically fold and the sealing cover opens to release the parachute. The battery module housing separates from the main body and drives the guiding mechanism to form a cone shape to guide the drone to descend, reducing the probability of getting caught in a tree.

[0009] As a further improvement to the above technical solution:

[0010] Rotary supports are fixed at all four corners of the outer wall of the fuselage body. One end of the wing is rotatably mounted in the rotary support via a rotating shaft. An extension protrusion is integrally formed on the top of the wing. Electromagnetic adsorption blocks are fixed at the four corners of the outer wall of the fuselage body. When the electromagnetic adsorption blocks are energized, they adsorb the extension protrusion to fix the wing. When the UAV is in an abnormality, the electromagnetic adsorption blocks are de-energized and release the extension protrusion.

[0011] As a further improvement to the above technical solution:

[0012] Multiple connecting brackets are fixed to the outer wall of the storage cavity. The connecting brackets are fixed to the top of the housing body by bolts. The bolt connection makes the storage cavity easy to disassemble for maintenance of the parachute.

[0013] As a further improvement to the above technical solution:

[0014] A pull rope II corresponding to the wing is fixed on the outer wall of the sealing cover. A positioning steel ball is set at the end of the pull rope II away from the sealing cover. Positioning slots are opened on the opposite sides of the electromagnetic adsorption block and the extension protrusion. The positioning steel ball is inserted into the positioning slot to lock the sealing cover. The sealing cover is bonded and fixed to the top of the parachute.

[0015] As a further improvement to the above technical solution:

[0016] The top of the storage cavity has an annular groove with a spring inside. The bottom of the spring is bonded to the bottom wall of the annular groove, and the top of the spring abuts against the sealing cover. When the sealing cover is unlocked, the spring releases energy and pushes it upward.

[0017] As a further improvement to the above technical solution:

[0018] The support mechanism includes two connecting rods fixed on both sides of the housing body. An extension rod is vertically fixed at the bottom of the connecting rod. The connecting rod and the extension rod are welded and fixed together and reinforced with ribs to improve the load-bearing strength.

[0019] As a further improvement to the above technical solution:

[0020] The guiding mechanism includes two support seats, with a connecting shaft rotatably mounted between them. An extension rod has an installation cavity, and the support seats are fixed to both ends of the installation cavity. An installation groove is provided on the inner side of the support seats. A torsion spring is sleeved on the connecting shaft and located in the installation groove. The two ends of the torsion spring are fixed to the connecting shaft and the installation groove, respectively. A guide film is fixed to the outer wall of the connecting shaft and wound around it. A rectangular opening is provided on the outer wall of the extension rod. The outer end of the guide film passes through the rectangular opening and cooperates with the battery module housing. When the battery module housing is pulled down, it causes the guide film to unfold, and the torsion spring assists in resetting.

[0021] As a further improvement to the above technical solution:

[0022] Pull rope Ⅲ is fixed in the middle of the opposite ends of the two guide films, and the two opposite ends are connected by elastic pull ropes. Two elastic inserts are fixed at the bottom of the battery module housing. The elastic inserts are engaged with pull rope Ⅲ to transmit tension. The elastic pull ropes ensure that the guide films are gathered into a cone shape.

[0023] As a further improvement to the above technical solution:

[0024] All three pull ropes, namely pull rope I, pull rope II, and pull rope III, are made of high-strength nylon rope. Pull rope I is fixed to the wing by quick-release buckles, which facilitates disassembly and maintenance.

[0025] As a further improvement to the above technical solution:

[0026] The outer side of plug I is provided with a guide bevel, and the contact surface between plug I and plug II is provided with a dustproof sealing ring. The guide bevel improves the insertion accuracy, and the dustproof sealing ring ensures stable power transmission.

[0027] The beneficial effects of this invention are as follows:

[0028] 1. The surveying and mapping device for unmanned aerial vehicles (UAVs) disclosed in this invention, when the UAV falls, the guide film quickly unfolds and assembles, encasing the originally uneven bottom of the fuselage (including easily snagged parts such as the gimbal and landing gear) in a smooth inverted cone. During descent, it can effectively part and slide through the intricate network of branches and leaves, fundamentally eliminating the possibility of mechanical interlocking between the fuselage structure and tree branches, ensuring that the UAV can penetrate the canopy and land on the ground, greatly reducing the risk of "losing while snagged on a tree".

[0029] 2. The surveying and mapping device for unmanned aerial vehicles (UAVs) disclosed in this invention utilizes the gravitational potential energy of the battery storage module, the heaviest component of the fuselage. In the critical moment of a complete power outage, the automatic detachment and descent of the battery storage module not only cuts off the dangerous power supply but also directly converts it into powerful mechanical force to pull the guide film unfold. This design eliminates the need for any backup batteries or motors, ensuring that the protective deformation action can still be executed 100% reliably even under extreme conditions where the electronic system is completely paralyzed.

[0030] 3. The UAV mapping device for exploration disclosed in this invention keeps the wings deployed when powered on normally. Once the power is cut off (a malfunction occurs), the electromagnetic force disappears and automatically triggers the folding program. Combined with the release of the parachute, it forms a pure physical emergency response chain that does not rely on flight control commands.

[0031] Other advantages, objectives, and features of the invention will be set forth in part in the description which follows, and in part will be apparent to those skilled in the art from the following examination, or may be learned from practice of the invention. The objectives and other advantages of the invention can be realized and obtained through the following description. Attached Figure Description

[0032] To make the objectives, technical solutions, and advantages of the present invention clearer, the preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings, wherein:

[0033] Figure 1 is a three-dimensional structural schematic diagram of the UAV mapping device for surveying according to the present invention;

[0034] Figure 2 is a schematic diagram of the structure of the UAV mapping device for surveying according to the present invention during its fall.

[0035] Figure 3 is a schematic diagram of the storage mechanism in this invention;

[0036] Figure 4 is a schematic diagram of the opening structure of the storage mechanism in this invention;

[0037] Figure 5 is a schematic diagram of the connection structure between the wing and the fuselage body in this invention;

[0038] Figure 6 is a schematic diagram of the battery storage module housing structure in this invention;

[0039] Figure 7 is a schematic diagram of the support mechanism structure in this invention;

[0040] Figure 8 is a schematic diagram of the installation structure of the guide mechanism in this invention.

[0041] Reference numerals: 1. UAV; 2. Storage mechanism; 3. Guiding mechanism; 4. Parachute; 10. Casing body; 101. Electromagnetic adsorption block; 102. Plug I; 11. Pull rope I; 12. Battery module housing; 121. Plug II; 122. Elastic insert; 13. Wing; 14. Support mechanism; 141. Connecting rod; 142. Extension rod; 143. Mounting cavity; 144. Rectangular opening; 16. Rotating support; 17. Rotating shaft; 18. Extension protrusion; 19. Positioning slot; 21. Storage cavity; 22. Sealing cover; 23. Connecting bracket; 24. Pull rope II; 25. Annular slot; 26. Spring; 27. Positioning steel ball; 31. Support base; 32. Connecting shaft; 33. Mounting groove; 34. Torsion spring; 35. Guide film; 36. Elastic pull rope; 37. Pull rope III. Detailed Implementation

[0042] The following specific examples illustrate the implementation of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention.

[0043] As shown in Figure 1, the surveying drone mapping device comprises a drone 1, a storage mechanism 2, and two guiding mechanisms 3. These components are mechanically connected and work together to achieve safety protection during normal surveying operations and in abnormal situations. The drone 1 is assembled from a fuselage body 10, a battery module housing 12, wings 13, and a support mechanism 14. The fuselage body 10 is made of lightweight aluminum alloy, with anodized surface treatment forming a dense oxide film, effectively improving corrosion resistance and surface hardness. The overall structural design balances strength and lightweight requirements. Multiple reinforcing ribs are located inside the fuselage body 10, enhancing overall rigidity without adding excessive weight. Pre-installed wiring channels facilitate circuit connections between components.

[0044] The battery module housing 12 is injection molded from engineering plastic, possessing excellent insulation and impact resistance. It houses the lithium battery pack, which is secured within the housing 12 by multiple buffer pads made of elastic rubber to absorb vibrations during flight and prevent damage to the battery pack from turbulence. As shown in Figure 6, the plug II 121 embedded at the top of the battery module housing 12 and the plug I 102 embedded at the bottom of the housing body 10 form a pluggable conductive structure. The outer side of plug I 102 has a guide bevel for precise alignment and insertion with plug II 121. Dustproof sealing rings are provided on the contact surfaces of both to effectively prevent dust and moisture from entering, ensuring stable power transmission. The insertion of plug I 102 into the housing body 10 uses an interference fit, ensuring no looseness or gaps after installation and guaranteeing reliable connection.

[0045] There are four wings 13, all made of carbon fiber composite material. This material is fatigue-resistant, lightweight, and high-strength, making it suitable for repeated folding and resistant to damage. As shown in Figure 5, rotating supports 16 are bolted to the four corners of the outer wall of the fuselage body 10. The rotating supports 16 are made of cast iron and have bearing holes inside. Deep groove ball bearings are installed in the bearing holes to reduce friction when the rotating shaft 17 rotates, thus extending its service life. One end of the wing 13 is rotatably mounted in a deep groove ball bearing via a stainless steel rotating shaft 17. The rotating shaft 17 has shoulders at both ends to restrict its axial movement. The connection between the rotating shaft 17 and the wing 13 is fixed by welding, and the weld is ground to ensure a smooth surface. An extension protrusion 18 is integrally formed on the top of the wing 13. The extension protrusion 18 is made of ferromagnetic material, and the connection surface with the wing 13 is rounded to avoid the risk of breakage due to stress concentration. The adsorption surface of the extension protrusion 18 is smooth to increase the contact friction with the electromagnetic adsorption block 101 and prevent accidental detachment. Electromagnetic adsorption blocks 101 are fixedly installed at the four corners of the outer wall of the fuselage body 10, corresponding to the extension protrusions 18. The outer surface of the electromagnetic adsorption block 101 is fitted with a mounting box and fixed to the mounting seat of the fuselage body 10 by screws. The mounting seat is integrally formed with the fuselage body 10 to ensure a stable installation. When the electromagnetic adsorption block 101 is energized, it generates magnetic force, which can firmly adsorb the extension protrusions 18, so that the wing 13 remains in a horizontally deployed state.

[0046] At each of the four bottom corners of the battery module housing 12, a pull rope I11 is fixed with screws. The pull rope I11 is made of high-strength nylon rope, which has good tensile strength and wear resistance. The end of the pull rope away from the battery module housing 12 is fixedly connected to the corresponding wing 13 near the outer end via a quick-release buckle. The quick-release buckle facilitates subsequent maintenance and replacement. When the wing 13 is horizontally deployed, the pull rope I11 is in a taut state, providing four-point support for the battery module housing 12, ensuring a tight fit between the battery module housing 12 and the fuselage body 10, and preventing detachment during flight.

[0047] As shown in Figure 3, the storage mechanism 2 is installed on the top of the housing body 10, and mainly includes a storage cavity 21, a sealing cover 22, and a parachute 4. The storage cavity 21 is a cylindrical structure made of ABS engineering plastic, with anti-slip texture on the inner wall to prevent the parachute 4 from sliding freely inside. Three connecting brackets 23 are evenly distributed on the outer wall of the storage cavity 21. The connecting brackets 23 are stamped from steel plates, and each connecting bracket 23 has two bolt holes. The connecting brackets 23 are fixedly connected to the mounting plane on the top of the housing body 10 by stainless steel bolts. The mounting plane has corresponding threaded holes pre-machined, and positioning pin holes are provided around the threaded holes to ensure that the connecting brackets 23 are installed accurately and are easy to disassemble, facilitating subsequent inspection and replacement of the parachute 4. The storage cavity 21 is used to house the folded parachute 4. The parachute 4 is made of high-strength nylon fabric with a waterproof surface to withstand severe weather. The connecting rope at the bottom is a high-strength nylon rope. The end of the connecting rope is fixed to a fixing ring on the bottom wall of the storage cavity 21 by a knot. The fixing ring and the storage cavity 21 are integrally formed. The fixing ring is also equipped with an anti-detachment pin to ensure that the connecting rope will not accidentally fall off.

[0048] The sealing cover 22 is made of lightweight plastic with uniform thickness. Its diameter matches the inner diameter of the storage cavity 21. It is bonded to the top of the parachute 4 with epoxy resin adhesive. A sealing layer is also provided at the bonding point to improve waterproof and dustproof performance and form a reliable seal for the storage cavity 21. As shown in Figure 4, four pull ropes II 24 are evenly fixed to the outer wall of the sealing cover 22. The pull ropes II 24 are made of the same material as the pull ropes I 11. The fixing point of each pull rope II 24 to the sealing cover 22 is reinforced with a reinforcing plate to increase the connection strength and prevent pull-out. The end of each pull rope II 24 away from the sealing cover 22 is fixed with a positioning steel ball 27 by crimping. The positioning steel ball 27 is made of stainless steel with a chrome-plated surface to improve wear resistance and surface smoothness and reduce frictional wear with the positioning slot 19. Both the electromagnetic adsorption block 101 and the extension protrusion 18 have positioning grooves 19 on their adjacent sides, which are adapted to the positioning steel ball 27. The positioning grooves 19 are hemispherical grooves with rounded edges to facilitate the smooth insertion and removal of the positioning steel ball 27. When the electromagnetic adsorption block 101 adsorbs the extension protrusion 18, the positioning steel ball 27 is precisely inserted into the positioning groove 19, forming a stable lock on the sealing cover 22. The top of the receiving cavity 21 has an annular groove 25 with a rectangular cross-section. A spring 26 is installed inside. The bottom end of the spring 26 is fixed to the bottom wall of the annular groove 25 with adhesive. The top end of the spring 26 is in close contact with the lower surface of the sealing cover 22 and is always in a compressed state, storing elastic potential energy.

[0049] As shown in Figure 7, there are two sets of support mechanisms 14, fixed on both sides of the housing body 10. Each set of support mechanisms 14 includes two connecting rods 141 and two extension rods 142. The connecting rods 141 are made of aluminum alloy and are fixed to the side wall of the housing body 10 by bolts. The weld joints are reinforced with fillet welds, which are treated with rust prevention and sprayed with anti-rust paint to avoid oxidation and corrosion. The extension rods 142 are also made of aluminum alloy and are welded perpendicularly to the connecting rods 141 to form a T-shaped support structure. The inner side of the weld joint is provided with reinforcing ribs to further improve the load-bearing strength. The extension rods 142 have an installation cavity 143 inside. The installation cavity 143 is a hollow structure with a circular cross-section, used to accommodate the guide mechanism 3.

[0050] As shown in Figure 8, the guide mechanism 3 is installed in the corresponding mounting cavity 143. Each guide mechanism 3 includes two support seats 31, a connecting shaft 32, a torsion spring 34, a guide diaphragm 35, an elastic pull rope 36, and a pull rope III 37. The support seats 31 are made of cast iron and are fixed to both ends of the mounting cavity 143 by bolts. Locating pins are provided around the bolt holes to ensure the accurate installation position of the support seats 31. Bearing holes are opened on the opposite surfaces of the two support seats 31 for installing the connecting shaft 32. The connecting shaft 32 is made of stainless steel and is rotatably installed in the bearing holes of the two support seats 31. Shoulders are provided at both ends of the connecting shaft 32 to restrict its axial movement and ensure rotational stability. The support base 31 has an inner groove 33, which is an annular groove. The torsion spring 34 is sleeved on the connecting shaft 32 and located inside the mounting groove 33. The two ends of the torsion spring 34 are respectively embedded in the slot of the connecting shaft 32 and the inner wall groove of the mounting groove 33. The embedded part is also reinforced by spot welding to prevent loosening. In the initial state, the torsion spring 34 is in its original state.

[0051] The guide film 35 is made of polyimide, which has good flexibility and strength and is not easily torn. Its edges are wrapped to further prevent wear, and the surface is coated with a wear-resistant coating to improve its service life. One end of the guide film 35 is fixed to the outer wall of the connecting shaft 32 by a pressure plate and bolts. The pressure plate is made of stainless steel to ensure a firm fixation. The other end passes through a rectangular opening 144 on the outer wall of the extension rod 142 and is equipped with a rubber pressure plate. The edges of the rectangular opening 144 are chamfered to avoid scratching the guide film 35. A pull rope III 37 is fixedly connected to the middle of the two guide films 35 at their adjacent ends. The pull rope III 37 is made of the same material as the pull rope I 11. Its fixing point to the guide film 35 is made by multi-strand winding and knotting, and then wrapped with heat shrink tubing to prevent wear and breakage. The two ends of the two guide films 35 at their adjacent ends are connected by an elastic pull rope 36. The elastic pull rope 36 is made of polyurethane, which has good elasticity and resilience. Its two ends are connected to the guide film 35 by crimp joints to increase the reliability of the connection and prevent detachment. Two sets of elastic inserts 122 are fixed at the bottom of the battery module housing 12 corresponding to the pull rope Ⅲ37. The elastic inserts 122 are made of rubber and are fixed to the bottom of the battery module housing 12 through the slot for easy replacement. The cross section of the elastic inserts 122 is C-shaped and the tip is rounded to avoid scratching the pull rope Ⅲ37. During the fall, they can be stuck on the pull rope Ⅲ37.

[0052] The normal operating state of the surveying UAV mapping device is as follows: When the electromagnetic adsorption block 101 is energized, it generates magnetic force, adsorbing the extension protrusion 18 on the top of the wing 13, keeping the four wings 13 in a horizontally deployed state. At this time, the pull rope I 111 is in a taut state, providing stable support for the battery module housing 12. Plug I 102 and plug II 121 are fully connected. The lithium battery pack inside the battery module housing 12 supplies power to the various electrical components of the UAV 1 through the plug structure, allowing the UAV 1 to perform surveying operations normally. The sealing cover 22 is locked by the positioning steel ball 27 at the end of the pull rope II 24, which is engaged in the positioning slot 19. The spring 26 is in a compressed state, and the parachute 4 remains folded and stored in the storage cavity 21. The sealing structure of the storage cavity 21 effectively protects the parachute 4 from external environmental influences. The torsion spring 34 in the guide mechanism 3 is in its original state, the guide film 35 remains wound around the connecting shaft 32, and the elastic pull rope 36 is at its natural length, ensuring that the guide mechanism 3 does not affect the normal flight of the UAV 1.

[0053] As shown in Figure 2, when the UAV 1 experiences an anomaly during surveying operations, such as loss of power or attitude control failure, the control system immediately cuts off the power supply to the electromagnetic adsorption block 101. The electromagnetic adsorption block 101 loses its magnetism and no longer adsorbs the extension protrusion 18. At this time, under the action of its own weight and the pulling force of the battery module housing 12, the wing 13 folds downward around the rotation axis 17, reducing the lateral cross-sectional area of ​​the fuselage and initially reducing the probability of being intercepted by tree branches. During the folding process, the rotation axis 17 rotates smoothly in the deep groove ball bearing without any jamming. Finally, the wing 13 fits against the side wall of the fuselage body 10.

[0054] When the wing 13 folds downwards, the positioning steel ball 27 disengages from the positioning slot 19, releasing the locking state of the sealing cover 22. At this time, the spring 26 in the annular slot 25 releases its elastic potential energy, generating an upward thrust that pushes the sealing cover 22 upwards. The sealing cover 22 then causes the parachute 4 to disengage from the storage cavity 21. Under the action of the airflow, the parachute 4 quickly unfolds, generating upward buoyancy, effectively slowing down the descent speed of the drone 1 and preventing the drone 1 from falling rapidly and causing damage.

[0055] As the wing 13 folds, the pull rope I 11 gradually loosens, and the battery module housing 12 loses its support and moves downward under its own weight. At this point, the heavy battery module does not become a burden during the fall, but instead becomes the power source for the protection system. Plug I 102 and plug II 121 smoothly disengage under the action of the guide ramp, and the battery module housing 12 completely separates from the fuselage body 10. As the battery module housing 12 moves downward, the elastic insert 122 at its bottom moves accordingly, causing the pull rope III 37 to move downward during the fall and pulling the two guide films 35 closer together, driving the connecting shaft 32 to rotate. Under the downward pull of the battery module housing 12, the two guide films 35 unfold synchronously downward, and the elastic pull rope 36 ensures that the two sides of the two guide films 35 converge inward, ultimately forming a conical structure. The conical structure acts as a guide during the descent of the drone 1, reducing the contact area between the side of the drone 1 and the tree branches. At the same time, the tip of the cone can push aside some small branches, making it easier for the drone 1 to descend along the axis of the cone, effectively reducing the probability of the drone 1 getting caught in the tree.

[0056] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A surveying and mapping device for unmanned aerial vehicles (UAVs), characterized in that, include: The drone (1) consists of a main body (10), a battery module housing (12), wings (13), and a support mechanism (14). There are four wings (13), which can be folded and are located at the four corners of the outside of the drone (1). The battery module housing (12) is located at the bottom of the main body (10). A plug I (102) is embedded at the bottom of the main body (10). A plug II (121) that is inserted into the top of the battery module housing (12) is embedded and is connected to the plug I (102). Pull ropes I (11) are fixed at the four corners of the bottom of the battery module housing (12). Pull ropes I (11) are fixedly connected to the corresponding wings (13) to support the battery module housing (12). The storage mechanism (2) is located on the main body. (10) The top includes a detachable storage cavity (21), a parachute (4) is provided inside the storage cavity (21), the bottom connecting rope of the parachute (4) is fixed to the bottom wall of the storage cavity (21), and a sealing cover (22) that cooperates with the wing (13) is provided on the top of the storage cavity (21); two guide mechanisms (3) are respectively located in the corresponding support mechanism (14) and cooperate with the battery module housing (12). When the drone is in an abnormal situation, the wing (13) automatically folds and opens the sealing cover (22) to release the parachute (4), the battery module housing (12) separates from the main body of the housing (10) and drives the guide mechanism (3) to form a cone shape to guide the drone to descend and reduce the probability of getting stuck in the tree.

2. The UAV mapping device for exploration according to claim 1, characterized in that, Rotary supports (16) are fixed at all four corners of the outer wall of the housing body (10). One end of the wing (13) is rotated and assembled in the rotating support (16) through a rotating shaft (17). An extension protrusion (18) is integrally formed on the top of the wing (13). Electromagnetic adsorption blocks (101) are fixed at the four corners of the outer wall of the housing body (10). The electromagnetic adsorption blocks (101) are energized to adsorb the extension protrusions (18) to fix the wing (13). When the UAV is abnormal, the electromagnetic adsorption blocks (101) are de-energized and release the extension protrusions (18).

3. The UAV mapping device for exploration according to claim 2, characterized in that, Multiple connecting brackets (23) are fixed to the outer wall of the storage cavity (21). The connecting brackets (23) are fixed to the top of the housing body (10) by bolts. The bolt connection makes it easy to disassemble the storage cavity (21) to maintain the parachute (4).

4. The UAV mapping device for exploration according to claim 2, characterized in that, The outer wall of the sealing cover (22) is fixed with a pull rope II (24) corresponding to the wing (13). A positioning steel ball (27) is provided at the end of the pull rope II (24) away from the sealing cover (22). Positioning slots (19) are provided on the opposite sides of the electromagnetic adsorption block (101) and the extension protrusion (18). The positioning steel ball (27) is inserted into the positioning slot (19) to lock the sealing cover (22). The sealing cover (22) is bonded and fixed to the top of the parachute (4).

5. The UAV mapping device for exploration according to claim 4, characterized in that, The top of the storage cavity (21) is provided with an annular slot (25), and a spring (26) is provided in the annular slot (25). The bottom end of the spring (26) is bonded to the bottom wall of the annular slot (25), and the top end is in contact with the sealing cover (22). When the sealing cover (22) is unlocked, the spring (26) releases energy and pushes it to pop up.

6. The UAV mapping device for exploration according to claim 5, characterized in that, The support mechanism (14) includes two connecting rods (141) fixed on both sides of the housing body (10). An extension rod (142) is vertically fixed at the bottom of the connecting rod (141). The connecting rod (141) and the extension rod (142) are welded and fixed together and reinforced with ribs to improve the load-bearing capacity.

7. The UAV mapping device for exploration according to claim 6, characterized in that, The guiding mechanism (3) includes two support seats (31), a connecting shaft (32) is rotatably provided between the support seats (31), an installation cavity (143) is provided in the extension rod (142), the support seats (31) are fixed at both ends of the installation cavity (143), an installation groove (33) is provided on the inner side of the support seats (31), a torsion spring (34) located in the installation groove (33) is sleeved on the connecting shaft (32), the two ends of the torsion spring (34) are fixed to the connecting shaft (32) and the installation groove (33) respectively, a guide film (35) is fixed on the outer wall of the connecting shaft (32), a rectangular opening (144) is provided on the outer wall of the extension rod (142), the outer end of the guide film (35) passes through the rectangular opening (144) and cooperates with the battery module housing (12), when the battery module housing (12) is pulled down, the guide film (35) is pulled up and the torsion spring (34) assists in resetting.

8. The UAV mapping device for exploration according to claim 7, characterized in that, Two guide films (35) are fixed with a pull rope III (37) at the middle of opposite ends. The two opposite ends are connected by an elastic pull rope (36). Two elastic inserts (122) are fixed at the bottom of the battery module housing (12). The elastic inserts (122) are engaged with the pull rope III (37) to transmit the tension. The elastic pull rope (36) ensures that the guide films (35) are gathered to form a cone shape.

9. The UAV mapping device for exploration according to claim 8, characterized in that, Pull rope I (11), pull rope II (24) and pull rope III (37) are all made of high-strength nylon rope. Pull rope I (11) is fixed to the wing (13) by quick-release buckles, which facilitates disassembly and maintenance.

10. The UAV mapping device for exploration according to claim 9, characterized in that, The outer side of plug I (102) is provided with a guide slope, and the contact surface between plug I (102) and plug II (121) is provided with a dustproof sealing ring. The guide slope improves the insertion accuracy, and the dustproof sealing ring ensures stable power transmission.

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