Modular multi-copter unmanned aerial vehicle

Abstract

This utility model discloses a modular multi-rotor unmanned aerial vehicle (UAV), including a first plate extending along a first direction and mounting seats for two second plates. The two second plates are fixedly connected to opposite sides of the first plate, forming a groove-shaped structure. A snap-fit ​​portion is provided on the inner wall of the second plate near the groove-shaped structure. A disassembly seat is provided with a guide structure and a locking component. The guide structure extends along the first direction, and the locking component is slidably connected to the guide structure along a second direction. The shape of the guide structure in its cross-section perpendicular to the first direction matches the shape of the groove-shaped structure. The guide structure can be slidably disposed within the groove-shaped structure along the first direction, and the locking component and the snap-fit ​​portion are in a snap-fit ​​state. Either the mounting seat or the disassembly seat is detachably fixedly connected to the UAV, while the other is used to carry a functional module. This utility model solves the problems of manual replacement of functional modules, low efficiency and task interruption, and the contradiction between energy and payload.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a modular multi-rotor UAV. Background Technology

[0002] Modular multi-rotor UAVs, with their core characteristics such as vertical takeoff and landing, hovering, and high maneuverability, have been widely used in numerous fields including military reconnaissance, logistics transportation, agricultural plant protection, and disaster relief, becoming indispensable tools in modern mission execution. As the complexity of actual missions continues to increase, the functional limitations of single UAVs are becoming increasingly apparent, making it difficult to meet diverse and challenging operational needs. Therefore, modular design and swarm collaboration are gradually becoming important development directions in this field. Modular design enables rapid replacement of functional equipment through standardized interfaces, flexibly adapting to different mission scenarios; swarm collaboration, through multi-UAV cooperation, effectively improves mission completion efficiency and operational coverage.

[0003] The current market demand for multi-rotor drones is mainly reflected in three aspects: First, mission diversity. Different operational scenarios require specific payloads, such as high-definition camera equipment for reconnaissance missions, dedicated cargo holds for logistics transportation, and spraying devices for agricultural plant protection. Second, high efficiency and collaboration. In complex environments, multi-drone formation operations can achieve complex tasks such as collaborative search and joint transportation. Third, autonomous intelligence. Drones are required to have capabilities such as autonomous landing, dynamic obstacle avoidance, and precise positioning to reduce human intervention and improve operational reliability.

[0004] However, traditional multi-rotor drone systems generally employ fixed-function designs and lack standardized modular interfaces. This means that function expansion or equipment replacement requires manual operation, which is not only inefficient but also disrupts mission continuity. For example, battery replacement and gimbal adjustment must be completed while the drone is stopped, making automated rapid replacement impossible. Furthermore, traditional models suffer from an inherent contradiction between energy and payload: limited battery energy density results in short flight time, while blindly increasing battery capacity increases the fuselage weight, further shortening the flight time; the power output limitations of motors and ESCs mean their payload capacity is typically only 20% to 50% of their own weight; and the rotor's energy conversion efficiency is low during hovering and low-speed flight, with most energy consumed in counteracting gravity rather than propulsion, severely restricting their application effectiveness in complex scenarios. Utility Model Content

[0005] To address some or all of the technical problems existing in the prior art, this utility model provides a modular multi-rotor drone that enables rapid disassembly and replacement of drone functional modules, and is compatible with drone gimbals and other equipment to automate the replacement of functional modules, thereby improving the efficiency of drone use.

[0006] The technical solution of this utility model is as follows:

[0007] A modular multi-rotor unmanned aerial vehicle (UAV) is provided, comprising:

[0008] The mounting base includes a first plate and two second plates that both extend along a first direction. The two second plates are fixedly connected to opposite sides of the first plate, and the three form a groove-shaped structure. The second plates are provided with snap-fit ​​parts on the inner wall of the groove-shaped structure.

[0009] The disassembly base is provided with a guide structure and a locking member. The guide structure extends along the first direction, and the locking member is slidably connected to the guide structure along the second direction. The shape of the guide structure in the cross section perpendicular to the first direction is adapted to the shape of the groove structure.

[0010] The guide structure is slidably disposed within the groove structure along the first direction, and the engaging member and the engaging part are engaged. Either the mounting base or the disassembly base is detachably fixedly connected to the UAV, while the other is used to carry the functional module.

[0011] In some alternative embodiments, the engaging structure includes two symmetrically arranged locking blocks that pass through the guide structure and engage with the engaging portion, and a pushing structure is provided between the two locking blocks to apply a pushing force that moves them away from each other.

[0012] In some optional embodiments, the guide structure is provided with two symmetrical sliding grooves along the second direction, the locking block includes a locking section and a force-bearing section, the locking sections of the two locking blocks are slidably disposed in the two sliding grooves respectively, and the pushing structure is disposed between the two force-bearing sections, the force-bearing section extends along a third direction, and the third direction, the second direction and the first direction are perpendicular to each other.

[0013] In some alternative embodiments, the pushing structure is a spring, and the force-bearing section extends along the second direction and is provided with a limiting ring, with the two ends of the spring respectively disposed within the two limiting rings.

[0014] In some optional embodiments, a trigger arm is provided on the side of the force-bearing segment away from the limiting ring. The trigger arm extends in a direction away from the force-bearing segment, and a pressing part is formed by extending the end of the trigger arm away from the force-bearing segment in a third direction. The pressing part is used to cooperate in pressing to release the engagement state between the locking member and the locking part.

[0015] In some optional embodiments, the disassembly base further includes a base body, the base body being provided with a central through groove arranged in a third direction and a limiting groove arranged in a second direction, the limiting groove communicating with the central through groove, and a bearing section extending in the second direction being provided at the end of the force-bearing section away from the snap-fit ​​section, the bearing section being slidably disposed in the limiting groove.

[0016] In some alternative embodiments, the end of the second plate away from the first plate is provided with a limiting structure extending in a second direction, and the distance between the two limiting structures is less than the span of the guide structure in the second direction.

[0017] In some alternative embodiments, the modular multi-rotor UAV also includes a fuselage, a support mechanism, and a bottom of the fuselage detachably fixed to the mounting base. The support mechanism includes four support frames connected to the bottom of the fuselage and a connecting rod located between two support frames on the same side.

[0018] In some alternative embodiments, a detachable battery connector is provided on the top of the body, the battery connector is configured with a battery mounting slot, the battery module of the drone is detachably disposed in the battery mounting slot, and an auxiliary pull-out structure is provided on the side of the battery module away from the power connection area to assist in the disassembly of the battery module.

[0019] The main advantages of this utility model's technical solution are as follows:

[0020] This utility model discloses a modular multi-rotor UAV. Functional modules can be quickly assembled and disassembled with the UAV via mounting and disassembly bases. It is compatible with equipment such as UAV hangar gimbals for automated replacement operations, eliminating the need for manual intervention. This effectively improves the efficiency of UAV use, avoids mission interruptions due to functional module replacement, and ensures mission continuity. Specifically, the combination of the guide structure and the slotted structure provides precise guidance, enabling rapid positioning of functional modules, significantly shortening assembly time and improving assembly accuracy. The snap-fit ​​and snap-connecting parts allow for rapid fixation after positioning, making the assembly logic simple and intuitive, ensuring reliable and stable connections, reducing operational difficulty, and increasing assembly success rate. The overall structural design is modular, allowing for flexible replacement of different functional payloads to meet diverse mission requirements such as military reconnaissance and logistics transportation, enhancing the UAV's scenario adaptability. The simple and reliable assembly method reduces the additional weight caused by complex connection structures, helping to alleviate the contradiction between energy and payload in traditional UAVs, indirectly improving endurance and operational efficiency. Attached Figure Description

[0021] The accompanying drawings, which are included to provide a further understanding of the embodiments of the present invention and constitute a part of this invention, illustrate exemplary embodiments of the present invention and, together with the description thereof, serve to explain the present invention and do not constitute an undue limitation thereof. In the drawings:

[0022] Figure 1 This is a three-dimensional structural diagram of a modular multi-rotor UAV provided in one embodiment of the present invention.

[0023] Figure 2 This is a three-dimensional structural diagram of a mounting base for a modular multi-rotor UAV provided in one embodiment of the present invention.

[0024] Figure 3 This is a three-dimensional structural diagram of a modular multi-rotor UAV disassembly base provided in one embodiment of the present utility model.

[0025] Figure 4 This is a three-dimensional structural diagram of a drone provided in one embodiment of the present utility model.

[0026] Figure 5 This is a three-dimensional structural diagram of a drone's battery module and battery connector after assembly, provided as an embodiment of the present invention.

[0027] Figure 6 This is a three-dimensional structural diagram of a battery connector provided in one embodiment of the present invention.

[0028] Figure 7 This is a three-dimensional structural diagram of a battery module provided in one embodiment of the present utility model.

[0029] Explanation of reference numerals in the attached figures:

[0030] 1. Mounting base; 11. First plate; 12. Second plate; 121. Limiting structure; 13. Slotted structure; 14. Snap-fit ​​part; 2. Disassembly base; 21. Guide structure; 22. Snap-fit ​​part; 221. Snap-fit ​​block; 2211. Snap-fit ​​section; 2212. Force-bearing section; 2213. Limiting ring; 2214. Trigger arm; 2215. Pressing part; 23. Pushing structure; 3. Base body; 31. Central through slot; 32. Limiting slot; 4. Body; 5. Support mechanism; 51. Support frame; 52. Connecting rod; 6. Battery connector; 61. Battery mounting slot; 7. Battery module; 71. Auxiliary pull-out structure. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be clearly and completely described below in conjunction with specific embodiments and corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without creative effort are within the scope of protection of this utility model.

[0032] The technical solutions provided by the embodiments of this utility model are described in detail below with reference to the accompanying drawings.

[0033] refer to Figures 1 to 3 This utility model provides a modular multi-rotor unmanned aerial vehicle (UAV), including: a mounting base 1 and a disassembly base 2. The mounting base 1 includes a first plate 11 extending along a first direction X and two second plates 12. The two second plates 12 are fixedly connected to opposite sides of the first plate 11, forming a groove-shaped structure 13. A snap-fit ​​portion 14 is provided on the inner wall of the second plate 12 near the groove-shaped structure 13. The disassembly base 2 is provided with a guide structure 21 and a snap-fit ​​component 22. The guide structure 21 extends along the first direction X, and the snap-fit ​​component 22 is slidably connected to the guide structure 21 along the second direction Y. The shape of the guide structure 21 in the cross section perpendicular to the first direction X is adapted to the shape of the groove-shaped structure 13. The guide structure 21 is slidably disposed within the groove-shaped structure 13 along the first direction X, and the snap-fit ​​component 22 and the snap-fit ​​portion 14 are in a snap-fit ​​state. Either the mounting base 1 or the disassembly base 2 is detachably fixedly connected to the UAV, and the other is used to carry a functional module.

[0034] In this embodiment, the functional module and the UAV can be quickly assembled and disassembled via mounting base 1 and disassembly base 2. This allows for automated replacement operations with equipment such as UAV hangar gimbals, eliminating the need for manual intervention, effectively improving UAV utilization efficiency, preventing mission interruptions due to functional module replacement, and ensuring mission continuity. The cooperation between the guide structure 21 and the slotted structure 13 provides precise guidance, enabling rapid positioning of the functional module, significantly shortening assembly time, and improving assembly accuracy. The snap-fit ​​component 22 and snap-fit ​​part 14 allow for rapid fixation after positioning. The assembly logic is simple and intuitive, the connection is reliable and stable, reducing operational difficulty and increasing assembly success rate. The overall structural design is adapted to the modular concept, allowing for flexible replacement of different functional payloads to meet diverse mission requirements such as military reconnaissance and logistics transportation, enhancing the UAV's scenario adaptability. The simple and reliable assembly method reduces the additional weight caused by complex connection structures, helping to alleviate the contradiction between energy and payload in traditional UAVs, indirectly improving endurance and operational efficiency.

[0035] Optionally, the first plate 11 and the two second plates 12 of the mounting base 1 are integrally formed or integrally formed, for example, by injection molding or by machining metal materials into one piece using CNC technology.

[0036] The one-piece molding structure reduces the assembly steps involving multiple parts, decreases the number of parts and assembly errors, and improves production efficiency and structural consistency. It also enhances the overall structural strength and rigidity of the mounting base 1, reducing the risk of engagement failure due to loose component connections and improving the long-term reliability of the quick-release mechanism. Furthermore, the one-piece molding process (such as injection molding, CNC machining within sliding grooves, and the installation of the pushing structure between the two stress-bearing sections) allows for a lighter structural design, reducing the weight of the mounting base 1 while maintaining strength, thus helping to further alleviate the conflict between the drone's energy and payload requirements.

[0037] Optionally, the guide structure 21 and the slot structure 13 can be adapted to be circular, triangular, square, rectangular, polygonal, etc., to meet the requirements of limiting and guiding.

[0038] It should be noted that the first direction X is the first horizontal direction. When establishing the flight space coordinate system of the UAV, the first direction X is the horizontal vertical axis and the second direction Y is the horizontal horizontal axis.

[0039] refer to Figure 3 The engaging component 22 includes two symmetrically arranged engaging blocks 221. The two engaging blocks 221 are symmetrically arranged and pass through the guide structure 21 to engage with the engaging part 14. A pushing structure 23 is provided between the two engaging blocks 221 to apply a pushing force that moves the two engaging blocks 221 away from each other.

[0040] In this embodiment, two symmetrically arranged locking blocks 221, in conjunction with the pushing structure 23, can automatically enter the locking part 14 when the guide structure 21 slides to the locking position, realizing automatic locking of the functional module without additional manual alignment or operation, thus improving the response speed and smoothness of automated replacement. Driving the two locking blocks 221 to displacement through the same pushing structure 23 simplifies the transmission logic, reduces independent driving components, makes the overall structure more compact, reduces the space occupied by the mechanism, and also reduces the number of parts, facilitating lightweight design.

[0041] The locking block 221 passes through the guide structure 21 and engages with the locking part 14. Combined with the continuous thrust of the pushing structure 23, it forms a bidirectional stable lock, enhancing the vibration resistance of the engagement, reducing the risk of functional modules becoming loose during flight, and improving connection reliability. During disassembly, simply overcoming the thrust of the pushing structure 23 is sufficient to simultaneously disengage the two locking blocks 221 from the locking part 14, achieving rapid unlocking. The operation logic is unified and simple, adapting to the high-efficiency operation requirements of automated equipment such as UAV hangar gimbals. The pushing structure 23 can be made of elastic cylinders, springs, rubber, silicone, etc.

[0042] refer to Figure 1 and Figure 3 In some exemplary embodiments of this utility model, the guide structure 21 is provided with two symmetrical sliding grooves along the second direction Y. The locking block 221 includes a locking section 2211 and a force-bearing section 2212. The locking sections 2211 of the two locking blocks 221 are slidably disposed in the two sliding grooves, and the pushing structure 23 is provided between the two force-bearing sections 2212. The force-bearing section 2212 extends along the third direction Z. The third direction Z, the second direction Y and the first direction X are perpendicular to each other.

[0043] In this embodiment of the invention, the sliding groove cooperates with the locking section 2211 to achieve the basic locking function, and also guides the locking section 2211 to accurately displace along the second direction Y, ensuring that the locking block 221 accurately enters the locking part 14 under the action of the pushing structure 23, thereby improving the accuracy and stability of the locking positioning. The sliding groove restricts the circumferential degree of freedom of the locking section 2211, preventing the locking block 221 from circumferentially deflecting during displacement and causing jamming, ensuring the smooth operation of the mechanism and improving long-term reliability.

[0044] The sliding groove reduces the requirement for the direction of force applied to the pushing structure 23, eliminating the need for strict control over the directional accuracy of the pushing force. This lowers the precision standards for structural processing and assembly, reducing production difficulty and costs. By constraining the locking section 2211 with the sliding groove, the auxiliary support design of the pushing structure 23 and the locking block 221 can be simplified, reducing redundant components and further optimizing the overall lightweight effect of the structure, meeting the requirements for optimized payload and energy consumption of UAVs.

[0045] Optionally, both the snap-fit ​​section 2211 and the load-bearing section 2212 are strip-shaped structures and are integral structures, which can be made of hard, lightweight metal materials.

[0046] It should be noted that the third direction Z is the vertical direction of the UAV's flight space coordinate system.

[0047] refer to Figure 1 and Figure 3 In some exemplary embodiments of this utility model, the pushing structure 23 is a spring, and the force-bearing section 2212 extends along the second direction Y and is provided with a limiting ring 2213. The two ends of the spring are respectively disposed in the two limiting rings 2213.

[0048] In this embodiment of the invention, the limiting ring 2213 provides a stable limiting installation position for the spring, eliminating the need for bonding or welding, thus simplifying the spring assembly process, reducing assembly difficulty, improving production efficiency, and avoiding the weight increase caused by additional fixing processes. The limiting ring 2213 can constrain the spring's offset when it is stretched or contracted under force, ensuring that the spring always applies a stable, mutually distancing thrust to the two force-bearing segments 2212, guaranteeing the reliability of the automatic engagement of the locking block 221, and reducing the risk of engagement failure due to spring offset.

[0049] The limiting ring 2213 reduces the requirements for spring dimensional accuracy and assembly position. Combined with the constraint of the sliding groove on the snap-fit ​​section 2211, it can accommodate a certain range of part tolerances, reducing the impact of machining and assembly errors on mechanism performance and lowering production difficulty. The integrated design of the limiting ring 2213 and the force-bearing section 2212 results in a simple and compact structure, eliminating the need for additional spring fixing components and further reducing the number of parts. Combined with the lightweight effect of the sliding groove, this contributes to a more optimized lightweight design for the overall mechanism.

[0050] refer to Figure 1 and Figure 3 In some exemplary embodiments of this utility model, a trigger arm 2214 is provided on the side of the force-bearing segment 2212 away from the limiting ring 2213. The trigger arm 2214 extends in a direction away from the force-bearing segment 2212, and the trigger arm 2214 extends in a third direction Z along one end away from the force-bearing segment 2212 to form a pressing part 2215. The pressing part 2215 is used to cooperate in pressing to release the engagement state between the locking member 22 and the locking part 14.

[0051] In this embodiment of the utility model, the structural design of the pressing part 2215 and the trigger arm 2214 allows for direct force application via manual or automated equipment (such as the robotic arm of a drone hangar) to quickly release the engagement state of the locking part 22 and the locking part 14, thereby improving the disassembly efficiency of the functional module and adapting to the need for rapid replacement.

[0052] The pressing part 2215 extends along the third direction Z and matches the force direction of the trigger arm 2214. The force applied is more in line with the operation trajectory (such as the movement of the robotic arm or the pressing habit of a human hand), reducing the difficulty of disassembly and reducing the risk of misoperation.

[0053] The trigger arms 2214 and the pressing part 2215 on both sides are symmetrically arranged. When pressed, the two locking blocks 221 can be driven to retract synchronously to ensure that the force is balanced during the locking and unlocking process, avoid one-sided jamming, and ensure smooth disassembly.

[0054] The structure achieves disassembly only through the extension design of the trigger arm 2214 and the pressing part 2215, without the need for additional driving components. It has a high degree of integration with the existing structure, does not add redundant weight, and meets the requirements of lightweight design.

[0055] The prominent design of the pressing part 2215 reduces the positioning accuracy requirements of the disassembly equipment (such as the robotic arm not needing to precisely align small parts), and improves its compatibility with automated disassembly equipment.

[0056] Furthermore, in some alternative solutions, the end of the pressing part 2215 away from the trigger arm 2214 is provided with a limiting end face away from the trigger arm 2214 in the second direction Y, which can be adapted to disassembly tools such as robotic arms for positioning operations.

[0057] refer to Figure 1 and Figure 3 In some exemplary embodiments of this utility model, the disassembly base 2 further includes a base body 3. The base body 3 is provided with a central through groove 31 arranged along the third direction Z and a limiting groove 32 arranged along the second direction Y. The limiting groove 32 communicates with the central through groove 31. The end of the force-bearing section 2212 away from the snap-fit ​​section 2211 is provided with a bearing section extending along the second direction Y. The bearing section is slidably arranged in the limiting groove 32.

[0058] In this embodiment of the invention, the central through groove 31 can precisely limit the movement position of the force-bearing segment 2212, preventing it from shifting along the first direction X or other non-preset directions, ensuring that the locking block 221 only moves stably along the second direction Y, and improving the accuracy of the locking and unlocking actions. The bearing segment and the limiting groove 32 slide together, which can not only further constrain the movement direction of the bearing segment and the connected force-bearing segment 2212 through the limiting groove 32 to prevent circumferential rotation or shaking, but also provide a clear benchmark for the assembly of the base body 3 and the force-bearing segment 2212, simplifying the assembly process and improving efficiency.

[0059] The design of the central through slot 31 and the limiting slot 32 allows for coordinated constraint of the motion trajectories of the force-bearing section 2212 and the load-bearing section, reducing component motion interference, lowering the risk of jamming, ensuring the smooth extension and retraction of the locking block 221, and improving the long-term reliability of the mechanism. The assembly and cooperation between the load-bearing section and the limiting slot 32 requires no additional fixing structure; positioning and motion constraint are achieved through a sliding connection. This results in high structural integration, reduces redundant parts, and contributes to overall lightweight design.

[0060] The through slots and limiting slots 32 of the base body 3 provide reasonable layout space for internal components (such as the force-bearing section 2212, springs, etc.), making the structure of the disassembly base 2 more compact, adaptable to the limited installation space of the UAV, and enhancing spatial adaptability. The base body 3 has a functional module mounted on the side opposite to the guide structure 21, providing an independent and stable installation carrier, avoiding spatial interference between the functional module and the quick-release parts, improving installation compatibility and stability, and adapting to different load layout requirements.

[0061] The load-bearing section and the locking component 22 connect the disassembly base 2, the mounting base 1, and the base body 3 into one unit, achieving structural reuse and reducing the number of parts. This makes the overall structure more compact, saving space, and reducing redundant weight, thus enhancing the lightweight effect. The integrated connection design enhances the collaborative stress-bearing capacity of each component, reduces stress concentration caused by the splicing of multiple components, improves the overall structural strength and vibration resistance of the quick-release mechanism, and ensures long-term reliability.

[0062] refer to Figure 1 and Figure 2 In some exemplary embodiments of this utility model, a limiting structure 121 extending along the second direction Y is provided at the end of the second plate 12 away from the first plate 11, and the distance between the two limiting structures 121 is less than the span of the guide structure 21 in the second direction Y.

[0063] The limiting structure 121 forms a downward limit on the guide structure 21 through size constraints, which can effectively prevent the guide structure 21 from detaching from the end of the groove structure 13 away from the first plate 11, avoiding the risk of functional modules falling off due to accidental loosening during the operation of the UAV, and improving connection safety.

[0064] The dimensional fit between the two limiting structures 121 and the guide structure 21 enhances the fit between the groove structure 13 and the guide structure 21, reduces the gap and wobble between them, improves the overall fit accuracy and structural rigidity, and optimizes the fit properties of the quick-release mechanism.

[0065] The limiting structure 121 ensures that the groove structure 13 and the guide structure 21 retain only a single direction of sliding freedom after assembly. Combined with the locking function of the locking component 22, it forms a dual fixing mechanism of "mechanical limiting + active locking", which greatly improves the structural stability after assembly and is especially suitable for the high-frequency vibration environment during UAV flight.

[0066] The single sliding degree of freedom design simplifies the assembly trajectory of the guide structure 21, allowing the functional module to be aligned simply by sliding along a preset direction during replacement, reducing the operational difficulty of automated equipment and improving disassembly and assembly efficiency.

[0067] Optionally, if the structural strength meets the requirements for use, weight reduction holes or wire harness holes can be provided on the mounting base 1, the disassembly base 2, and the base body 3 to allow wires to pass through or reduce the overall weight.

[0068] Optionally, the distance between the side of the limiting structure 121 away from the first plate 11 and the base body 3 is adapted to the thickness of the trigger arm 2214 in the third direction Z, and the two can be in clearance fit.

[0069] Optionally, when the engaging member 22 compresses the spring, the distance between the two pressing parts 2215 is slightly greater than the distance between the two second plates 12 on opposite sides.

[0070] Specifically, the application of the aforementioned modular multi-rotor UAVs enables rapid assembly and disassembly of functional modules. This allows for quick replacement of different payloads to meet the functional requirements of the UAV, flexibly adapting to diverse mission scenarios such as military reconnaissance, logistics transportation, and agricultural plant protection, thereby enhancing the UAV's mission adaptability and multi-scenario operational capabilities. Utilizing the automated replacement function of the quick-release mechanism, the UAV can be adapted to equipment such as UAV hangars and gimbals to automatically change functional modules, reducing manual intervention, shortening mission intervals, and improving overall operational efficiency and continuity. The lightweight and compact design of the quick-release mechanism reduces the weight and space occupied by the UAV, helping to alleviate the inherent contradiction between the UAV's energy and payload, indirectly improving endurance and effective operating time.

[0071] The specific structure and beneficial effects of the modular multi-rotor UAV are detailed in the above embodiments and will not be repeated here.

[0072] refer to Figure 4 In combination with the actual structure, the UAV also includes a body 4, a support mechanism 5, and the bottom of the body 4 is detachably fixed to the mounting base 1. The support mechanism 5 includes four support frames 51 connected to the bottom of the body 4 and a connecting rod 52 located between two support frames 51 on the same side.

[0073] Compared to the traditional two-support rod structure, the support mechanism 5, consisting of four support frames 51, improves the overall stability of the drone during takeoff and landing, reduces fuselage sway, and lowers the risk of tipping over due to unstable support, making it particularly suitable for complex terrain operation scenarios.

[0074] The connecting rod 52 between the two support frames 51 on the same side enhances the overall structural integrity of the support mechanism 5, and can evenly distribute the impact force of lifting and lowering to each support frame 51, avoid overload deformation of a single support rod, extend the service life of the support mechanism 5, and improve the durability of the equipment.

[0075] Four support frames 51 surround the mounting base 1 to form a protective structure, which can block external forces such as collisions and friction from acting directly on the mounting base 1 and quick-release mechanism when the drone takes off, lands, is transported or operated, reducing the risk of damage to key components, providing physical protection for the quick-release mechanism and ensuring its long-term stable operation.

[0076] refer to Figures 5 to 7 The top of the body 4 is provided with a detachable battery connector 6. The battery connector 6 is constructed with a battery mounting slot 61. The battery module 7 of the drone is detachably installed in the battery mounting slot 61. An auxiliary pull-out structure 71 is provided on the side of the battery module 7 away from the power connection area to assist in the removal of the battery module 7.

[0077] The detachable design of the battery connector 6, in conjunction with the battery mounting slot 61, enables quick assembly and disassembly of the battery module 7. This facilitates efficient battery replacement during mission breaks, reduces drone downtime, and enhances continuous operation capability. The battery mounting slot 61 provides precise positioning and stable constraint for the battery module 7, ensuring reliable battery connection during flight, preventing power outages due to vibration, and improving electrical safety.

[0078] The auxiliary pull-out structure 71 simplifies the disassembly of the battery module 7, allowing for easy removal even when the battery is tightly fitted to the mounting slot. This reduces the difficulty of manual operation and adapts to the need for rapid replacement. The overall structure balances installation stability and ease of disassembly, enabling battery replacement without complex tools or professional skills. This enhances the adaptability of the drone for battery maintenance in field, emergency, and other scenarios, ensuring mission continuity.

[0079] Optionally, the body is provided with a mounting slot for the battery connector 6, and a foolproof structure is provided between the mounting slot and the battery connector 6, and a foolproof structure is provided between the battery mounting slot 61 and the battery module 7.

[0080] In one specific embodiment, it can be applied to a hexacopter drone, which adopts a modular design. The multi-rotor drone has a weight of no more than 4 kg, a maximum payload of no less than 6 kg, and a flight time of no less than 30 minutes. It can support automatic replacement of modular payloads such as batteries, gimbals, and bomb disposal devices. The appearance of the modular hexacopter drone platform can be referenced. Figure 4 .

[0081] To facilitate the fixing of data transmission and image transmission antennas and RTK antennas, the top of the device is set as the antenna fixing layer.

[0082] To facilitate the installation of RTK receiver modules, flight controllers, airborne computing devices, and other equipment, a device placement layer is designed in the middle of the fuselage, where airborne equipment such as gyroscopes, transmitters, and controllers are placed.

[0083] Specifically, in this embodiment of the invention, the support mechanism 5 includes four support frames 51 connected to the bottom of the body 4 and a connecting rod 52 located between two support frames 51 on the same side.

[0084] Specifically, in this embodiment of the invention, the battery can be modularized to form a battery module 7, the battery connector 6 forms a battery mounting slot 61, and the top of the battery module 7 is provided with an auxiliary pull-out structure 71.

[0085] Furthermore, a mounting slot for the battery connector 6 is provided on the fuselage, and the battery module 7 can be installed into the mounting slot and removed from the modular multi-rotor drone by means of the auxiliary pull-out structure 71.

[0086] Secondly, in this embodiment of the invention, a mounting base 1 and a disassembly base 2 are provided to form a modular multi-rotor UAV, which allows other modular components to be easily mounted onto the UAV. See the figures and the foregoing embodiments for details.

[0087] Therefore, modular components can be easily installed on or removed from multi-rotor drones by using a robotic arm that is compatible with gimbals or drone hangars.

[0088] This embodiment of the modular multi-rotor UAV structure employs a modular payload quick-change device, designed with mechanical gripping interfaces, power supply contacts, and communication interfaces supporting automatic replacement of modular components such as batteries and gimbals. By reserving universal interfaces, seamless integration and expansion of different functional modules are achieved, avoiding customized modifications. Precise landing is achieved by combining a visual camera and RTK equipment. Four support frames enhance structural strength, enabling a maximum payload of over 6 kg (payload ratio of 150%) with a weight of less than 4 kg and an endurance of over 30 minutes. Furthermore, the layered structure design includes separate antenna mounting layers and equipment placement layers, optimizing space utilization and electromagnetic compatibility.

[0089] Compared with existing technologies, the modular multi-rotor UAV of this invention has the following advantages:

[0090] Modular design: Modular multi-rotor UAVs support rapid replacement of modular payloads such as batteries, gimbals, and bombing devices. Seamless integration is achieved through standardized interfaces (mechanical gripping interface, power supply contacts, and communication interface), which significantly improves mission flexibility and maintenance efficiency.

[0091] Lightweight and High Payload Capacity: Utilizing a six-rotor layout, the aircraft achieves a maximum payload capacity of over 6kg while maintaining a weight of no more than 4kg, with a flight time of at least 30 minutes, thus balancing lightweight design with high payload capacity. A layered design (antenna mounting layer, equipment placement layer) rationally distributes weight, preventing center of gravity shift from affecting flight stability.

[0092] Enhanced structural stability: The traditional two support rods of the drone have been replaced with four support frames51, improving landing stability and impact resistance, and reducing the risk of crashes. The separate design of the antenna mounting layer and equipment placement layer reduces signal interference and facilitates equipment maintenance and upgrades.

[0093] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Additionally, the terms "front," "back," "left," "right," "upper," and "lower" in this document refer to the placement shown in the accompanying drawings.

[0094] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and not to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A modular multi-copter drone, characterized in that, include: The mounting base includes a first plate and two second plates that both extend along a first direction. The two second plates are fixedly connected to opposite sides of the first plate, and the three form a groove-shaped structure. The second plates are provided with snap-fit ​​parts on the inner wall of the groove-shaped structure. The disassembly base is provided with a guide structure and a locking member. The guide structure extends along the first direction, and the locking member is slidably connected to the guide structure along the second direction. The shape of the guide structure in the cross section perpendicular to the first direction is adapted to the shape of the groove structure. The guide structure is slidably disposed within the groove structure along the first direction, and the engaging member and the engaging part are engaged. Either the mounting base or the disassembly base is detachably fixedly connected to the UAV, while the other is used to carry the functional module.

2. The modular multi-copter unmanned aerial vehicle of claim 1, wherein, The engaging component includes two symmetrically arranged locking blocks. The two locking blocks are symmetrically arranged and pass through the guide structure to engage with the engaging part. A pushing structure is provided between the two locking blocks to apply a pushing force that moves the two locking blocks away from each other.

3. A modular multi-rotor UAV according to claim 2, characterized in that, The guide structure is provided with two symmetrical sliding grooves along the second direction. The locking block includes a locking section and a force-bearing section. The locking sections of the two locking blocks are slidably disposed in the two sliding grooves, and the pushing structure is provided between the two force-bearing sections. The force-bearing section extends along a third direction. The third direction, the second direction, and the first direction are perpendicular to each other.

4. A modular multi-rotor UAV according to claim 3, characterized in that, The pushing structure is a spring, and the force-bearing section extends along the second direction and is provided with a limiting ring. The two ends of the spring are respectively disposed in the two limiting rings.

5. A modular multi-rotor UAV according to claim 4, characterized in that, A trigger arm is provided on the side of the force-bearing section away from the limiting ring. The trigger arm extends in a direction away from the force-bearing section, and a pressing part is formed by extending the end of the trigger arm away from the force-bearing section in a third direction. The pressing part is used to cooperate in pressing to release the engagement state between the locking member and the locking part.

6. A modular multi-rotor unmanned aerial vehicle according to claim 3, characterized in that, The disassembly base also includes a base body, which is provided with a central through groove arranged in a third direction and a limiting groove arranged in a second direction. The limiting groove is connected to the central through groove. The end of the force-bearing section away from the snap-fit ​​section is provided with a bearing section extending in the second direction. The bearing section is slidably disposed in the limiting groove.

7. A modular multi-rotor unmanned aerial vehicle according to any one of claims 1 to 6, characterized in that, The second plate has a limiting structure extending in a second direction at the end away from the first plate, and the distance between the two limiting structures is less than the span of the guide structure in the second direction.

8. A modular multi-rotor unmanned aerial vehicle according to claim 7, characterized in that, The drone also includes a body, a support mechanism, and the bottom of the body is detachably fixed to the mounting base. The support mechanism includes four support frames connected to the bottom of the body and a connecting rod located between two support frames on the same side.

9. A modular multi-rotor unmanned aerial vehicle according to claim 8, characterized in that, The top of the body is provided with a detachable battery connector, which has a battery mounting slot. The battery module of the drone is detachably installed in the battery mounting slot, and the side of the battery module away from the power connection area is provided with an auxiliary pull-out structure to assist in the removal of the battery module.

Images