Eight-rotor unmanned aerial vehicle

Abstract

The invention relates to an eight-rotor unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, the eight-rotor unmanned aerial vehicle comprises a fuselage mechanism, rotor mechanisms and a control system, the rotor mechanisms are arranged on the peripheral side of the fuselage mechanism, the control system is arranged in the fuselage mechanism, and a loading mechanism is arranged at the bottom of the fuselage mechanism; the fuselage mechanism supports the rotor mechanisms, the control system and the loading mechanism, the rotor mechanisms generate distributed lift force through the eight groups of rotor mechanisms so as to change the lifting and flying attitude of the fuselage mechanism, the loading mechanism is convenient for loading of the unmanned aerial vehicle, and the control system adjusts the rotating speed of each rotor in real time so as to realize attitude control; the bottom loading mechanism provides an effective load bearing space, the control system forms a stable supporting frame for a top plate-bottom plate structure of the rotor wing mechanism through a collection sensor, all-directional thrust vector control is achieved through circumferentially-arranged rotor wings, the anti-crosswind capacity is improved through the eight-rotor-wing structure, the lifting stability of the unmanned aerial vehicle is improved, and the unmanned aerial vehicle is suitable for being used in the field of unmanned aerial vehicles. And the load capacity of the unmanned aerial vehicle is further improved.

Description

TECHNICAL FIELD

[0001] The application relates to the unmanned aerial vehicle technical field, in particular to an eight-rotor unmanned aerial vehicle. BACKGROUND

[0002] In recent years, multi-rotor unmanned aerial vehicles have been widely applied in civil and industrial fields due to their vertical take-off and landing, hovering, maneuvering flexibility and other advantages. The mainstream multi-rotor unmanned aerial vehicles include four-rotor, six-rotor and eight-rotor types. The four-rotor and six-rotor types occupy the market dominant position due to their simple structure and low cost, but their stability, load capacity and wind resistance are poor.

[0003] Therefore, with the increasing requirements of application scenarios on the performance of unmanned aerial vehicles, how to optimize energy consumption and controllability while ensuring flight stability has become a key direction of technical development. SUMMARY

[0004] In order to solve the defects in the above-mentioned technology, the application provides an eight-rotor unmanned aerial vehicle.

[0005] The eight-rotor unmanned aerial vehicle provided by the application adopts the following technical scheme: An eight-rotor unmanned aerial vehicle includes a body mechanism, a rotor mechanism and a control system. The rotor mechanism is arranged on the side of the body mechanism, the control system is arranged in the body mechanism, and the bottom of the body mechanism is provided with a load carrying mechanism.

[0006] In an optional embodiment, the body mechanism includes a horizontally arranged top plate and a bottom plate, the top plate and the bottom plate are connected by a plurality of vertically arranged fixed columns, a plurality of support plates are arranged horizontally on the fixed columns between the top plate and the bottom plate, a protective plate and a heat dissipation plate are arranged around the top plate and the bottom plate respectively, and the protective plate and the heat dissipation plate are connected with the fixed columns by fixing members respectively.

[0007] In an optional embodiment, the rotor mechanism includes a limiting plate, the limiting plate is arranged at the top of the plurality of fixed columns and is fixedly connected with the bottom of the top plate, a support arm is fixedly arranged at each of the four corners of the limiting plate, a take-off and landing assembly is fixedly arranged on the upper and lower sides of the middle part of the support arm respectively, the take-off and landing assembly includes a stabilizing plate, the stabilizing plate is arranged on the support arm, an output motor is fixedly arranged on the stabilizing plate, a lifting paddle is drivingly arranged at the output end of the output motor, and two buffer washers are symmetrically arranged between the stabilizing plate and the support arm.

[0008] In one optional embodiment, the other ends of the plurality of support arms are respectively fixedly connected to a first fixing ring. The support arm is provided with a plurality of slots, and a second fixing ring perpendicular to the first fixing ring is locked in the slot. A first locking member is locked at the connection between the first fixing ring and the second fixing ring. The first fixing ring is provided with a first curved groove, and the first curved groove is locked to a second curved groove on a third fixing ring by a locking connector. The top ends of the second fixing ring and the third fixing ring are fixedly connected by a first adapter. A locking plate is fixedly provided at the bottom of the base plate, and the bottom ends of the second fixing ring and the third fixing ring are located between the base plate and the locking plate.

[0009] In one optional embodiment, the latch includes a second latch, which is latched at the intersection of the first and second bends and fixed by bolts. A balance plate is fixedly provided on the side of the second latch away from the body mechanism, and a balance block is latched on the outside of the balance plate.

[0010] In one optional embodiment, the first adapter includes a first locking plate and a second locking plate, which are respectively fixedly disposed on the upper and lower sides of the top of the second fixing ring and the third fixing ring, and a cover plate is fixedly disposed on the top of the first locking plate by bolts.

[0011] In one optional embodiment, the loading mechanism includes a load-bearing plate, which is bolted to the bottom of the base plate, and a loading box is fixedly disposed below the load-bearing plate.

[0012] In one optional embodiment, the control system includes a lithium battery pack, a power distribution module, a flight control motherboard, an IMU sensor, and a wireless communication module. The lithium battery pack, power distribution module, flight control motherboard, IMU sensor, and wireless communication module are respectively mounted on multiple support plates. The lithium battery pack is electrically connected to the power distribution module. The multiple output motors, flight control motherboard, IMU sensor, and wireless communication module are respectively electrically connected to the power distribution module. The flight control motherboard is electrically connected to the IMU sensor, electrically connected to the wireless communication module, and electrically connected to the multiple output motors.

[0013] In summary, this application includes at least one of the following beneficial technical effects: 1. The octocopter configuration has higher redundancy than the quadcopter or hexacopter configuration, and can still maintain basic flight even if a single rotor fails; 2. Modular design facilitates maintenance and replacement; 3. The circumferentially evenly distributed rotor mechanism enhances the ability to resist crosswinds. Attached Figure Description

[0014] Figure 1This is a schematic diagram of the overall structure provided in the embodiments of this application; Figure 2 This is a schematic diagram of the fuselage mechanism structure provided in the embodiments of this application; Figure 3 yes Figure 1 A magnified view of a section at point A in the middle; Figure 4 yes Figure 1 A magnified view of a section at point B in the middle; Figure 5 This is a schematic diagram of a portion of the rotor mechanism provided in an embodiment of this application; Figure 6 This is a schematic diagram of the exploded structure of the rotor mechanism provided in the embodiment of this application.

[0015] Explanation of reference numerals in the attached drawings: 1. Fuselage mechanism; 11. Top plate; 12. Bottom plate; 13. Fixing column; 14. Support plate; 15. Protective plate; 16. Heat dissipation plate; 17. Fixing component; 2. Rotor mechanism; 21. Limiting plate; 22. Support arm; 23. Take-off and landing assembly; 231. Stabilizing plate; 232. Output motor; 233. Lifting blade; 234. Buffer pad; 235. First fixing ring; 236. Slot; 237. 238. Second fixing ring; 239. First clamping element; 240. First curved groove; 240. Clamping device; 2401. Second clamping element; 2402. Balance block; 2403. Balance plate; 241. Third fixing ring; 242. Second curved groove; 243. First adapter; 2431. First locking plate; 2432. Second locking plate; 2433. Cover plate; 244. Clamping plate; 3. Loading mechanism; 31. Loading plate; 32. Loading box. Detailed Implementation

[0016] The technical solutions of this application will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0017] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0018] In the description of this application, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0019] Furthermore, the technical features involved in the different embodiments of this application described below can be combined with each other as long as they do not conflict with each other.

[0020] The present invention provides the following embodiments. Example 1

[0021] This application discloses an octocopter unmanned aerial vehicle, referring to... Figures 1-2 It includes a fuselage mechanism 1, a rotor mechanism 2 and a control system. The rotor mechanism 2 is disposed around the fuselage mechanism 1, the control system is disposed inside the fuselage mechanism 1, and a cargo-carrying mechanism 3 is disposed at the bottom of the fuselage mechanism 1.

[0022] The working principle and beneficial effects of the above technical solution are as follows: The fuselage mechanism 1 supports the rotor mechanism 2, the control system, and the cargo handling mechanism 3. The rotor mechanism 2 generates distributed lift through eight sets of rotor mechanisms 2, thereby changing the ascent, descent, and flight attitude of the fuselage mechanism 1. The cargo handling mechanism 3 facilitates cargo carrying for the UAV. The control system adjusts the rotation speed of each rotor in real time to achieve attitude control. The bottom cargo handling mechanism 3 provides effective payload carrying space. The control system collects sensors to form a stable support frame for the top plate 11-bottom plate 12 structure of the rotor mechanism 2. The circumferentially arranged rotors achieve all-round thrust vector control. The eight-rotor configuration has higher redundancy than the four-rotor or six-rotor configuration. It can still maintain basic flight even when a single rotor fails. The modular design facilitates maintenance and replacement. The independent cargo handling space at the bottom achieves physical isolation between the transport function and the flight control system. The circumferentially evenly distributed rotor mechanism 2 improves the crosswind resistance, enhances the stability of the UAV's ascent and descent, improves maneuverability, further reduces energy consumption, and improves the UAV's load capacity.

[0023] like Figures 1-2 As shown, the fuselage mechanism 1 includes a horizontally arranged top plate 11 and a bottom plate 12. The top plate 11 and the bottom plate 12 are connected by a plurality of vertically arranged fixing columns 13. A plurality of support plates 14 are horizontally arranged on the fixing columns 13 between the top plate 11 and the bottom plate 12. Protective plates 15 and heat dissipation plates 16 are respectively arranged around the top plate 11 and the bottom plate 12. The protective plates 15 and the heat dissipation plates 16 are respectively connected to the fixing columns 13 by fixing members 17.

[0024] The working principle and beneficial effects of the above technical solution are as follows: a box-shaped anti-torsional frame is formed by the double-layer structure of the top plate 11 and the bottom plate 12. The top plate 11 and the bottom plate 12 are fixed and limited as a whole by the fixing column 13. The fixing column 13 is fixedly connected to the protective plate 15 and the heat dissipation plate 16 between the top plate 11 and the bottom plate 12 by the fixing component 17. The fixing column 13 bears the main axial load, the support plate 14 provides lateral stiffness, the protective plate 15 forms a collision buffer, and the heat dissipation plate 16 uses the airflow of the flight to actively dissipate heat. The layered structure design realizes the scientific distribution of load. The combination of the fixing column 13 and the support plate 14 forms a three-dimensional truss structure that is lightweight and high-strength. The detachable protective plate 15 is designed for easy replacement of damaged parts. The directional heat dissipation plate 16 improves the heat dissipation efficiency of electronic components.

[0025] like Figures 1-3 As shown, the rotor mechanism 2 includes a limiting plate 21, which is disposed on the top of the plurality of fixed columns 13 and fixedly connected to the bottom of the top plate 11. Support arms 22 are fixedly disposed at the four corners of the limiting plate 21. Take-off and landing components 23 are fixedly disposed on the upper and lower sides of the middle part of the support arm 22. The take-off and landing components 23 include a stabilizing plate 231, which is disposed on the support arm 22. An output motor 232 is fixedly disposed on the stabilizing plate 231. The output end of the output motor 232 is driven by a lifting blade 233. Two buffer pads 234 are symmetrically disposed between the stabilizing plate 231 and the support arm 22.

[0026] The working principle and beneficial effects of the above technical solution are as follows: the fixed column 13 fixes the limiting plate 21 to support the rotor mechanism 2. The four corners of the limiting plate 21 fix the support arm 22 respectively. The four-point symmetrical layout of the support arm 22 ensures torque balance. The support arm 22 limits the take-off and landing assembly 23. The lift generated by the take-off and landing assembly 23 realizes the take-off and landing of the UAV. The support arm 22 serves as the mounting reference surface for the limiting plate 21 of the rotor mechanism 2. The support arm 22 forms a cantilever beam structure. The double buffer pads 234 constitute a two-stage shock absorption system to reduce vibration transmission. The stabilizing plate 231 forms a motor mounting platform and a fairing. The lifting blades 233 adopt a variable pitch design. The stabilizing plate 231 also has a flow guiding function to improve aerodynamic efficiency. The modular motor installation method supports quick replacement.

[0027] like Figure 1 , Figure 3 , Figure 4As shown, the other ends of the multiple support arms 22 are respectively fixedly connected to the first fixing ring 235. The support arm 22 is provided with multiple slots 236. The slots 236 are fitted with second fixing rings 237 that are perpendicular to the first fixing ring 235. The connection between the first fixing ring 235 and the second fixing ring 237 is fitted with a first locking member 238. The first fixing ring 235 is provided with a first curved groove 239. The first curved groove 239 is fitted with a second curved groove 242 on the third fixing ring 241 through a locking connector 240. The top ends of the second fixing ring 237 and the third fixing ring 241 are fixedly connected through a first adapter 243. The bottom of the base plate 12 is fixedly provided with a locking plate 244. The bottom ends of the second fixing ring 237 and the third fixing ring 241 are located between the base plate 12 and the locking plate 244.

[0028] The working principle and beneficial effects of the above technical solution are as follows: the support arm 22 provides multi-point support and fixation for the first fixed ring 235. The first fixed ring 235, the second fixed ring 237, and the third fixed ring 241 are fixed by snapping together through the slot 236. The first fixed ring 235 uses the first clip 238 to cross-connect the second fixed ring 237. The first fixed ring 235, the second fixed ring 237, and the third fixed ring 241 form an orthogonal ring frame. The orthogonal ring structure improves the overall bending stiffness. The slot 236-bolt connection enables rapid assembly. The detachable snap-connection design reduces the transportation volume. The first curved groove 239 of the first fixed ring 235 and the second curved groove 242 of the third fixed ring 241 are snapped together to form a spatial truss structure. The multi-directional constraint design effectively suppresses the resonance phenomenon, and the curved groove snap-connection mechanism realizes automatic adjustment of the pre-tightening force, which enhances the connection strength and does not affect the stability of the UAV. The card plate 244 provides bottom constraint. Example 2

[0029] Based on Example 1, such as Figure 5 , Figure 6 As shown, the latch 240 includes a second latch 2401. The second latch 2401 is latched and fixed by bolts at the intersection of the first bend 239 and the second bend 242. A balance plate 2403 is fixedly provided on the side of the second latch 2401 away from the body mechanism 1. A balance block 2402 is latched on the outside of the balance plate 2403.

[0030] The working principle and beneficial effects of the above technical solution are as follows: the cross-shaped clamp forms a four-way limiting constraint to fix the first curved groove 239 and the second curved groove 242, thereby increasing the connection strength and stability of the first fixed ring and the third fixed ring 241. The second clamp 2401 directly and indirectly fixes the balance plate 2403 and the balance block 2402. The balance plate 2403 and the balance block 2402 serve as a counterweight adjustment mechanism. The balance block 2402 achieves dynamic mass balance through sliding adjustment. Example 3

[0031] Based on Example 1, such as Figure 4 , Figure 6 As shown, the first adapter 243 includes a first locking plate 2431 and a second locking plate 2432. The first locking plate 2431 and the second locking plate 2432 are respectively fixedly disposed on the upper and lower sides of the top of the second fixing ring 237 and the third fixing ring 241. A cover plate 2433 is fixedly disposed on the top of the first locking plate 2431 by bolts.

[0032] The working principle and beneficial effects of the above technical solution are as follows: the first locking plate 2431 and the second locking plate 2432 fix the top of the second fixing ring 237 and the third fixing ring 241 with bolts. The upper and lower locking plates form a closed force flow path. The cover plate 2433 further secures the top of the first locking plate 2431, the second locking plate 2432, the second fixing ring 237 and the third fixing ring 241 with bolts. The double locking plate structure improves the fatigue life of the nodes, the bolt preload controls the connection stiffness, the transition angle adapts to the deformation of the frame, and the easy disassembly design shortens the maintenance time. Example 4

[0033] Based on Example 1, such as Figure 2 As shown, the loading mechanism 3 includes a load plate 31, which is bolted to the bottom of the base plate 12, and a loading box 32 is fixedly installed below the load plate 31.

[0034] The working principle and beneficial effects of the above technical solution are as follows: the load plate 31 is fixedly connected to the base plate 12 by bolts, and the cargo box 32 is fixedly connected to the load plate 31 by bolts. The load plate 31 facilitates the drone to carry heavy objects. The working principle is as follows: the load plate 31 is connected by bolts to achieve quick assembly and disassembly. The cargo box 32 adopts a honeycomb sandwich structure and a modular design to support multiple mission loads. The quick-release structure enables rapid load replacement. The honeycomb structure makes the drone lightweight while improving the payload ratio. Example 5

[0035] Based on Example 1, such as Figures 2-3As shown, the control system includes a lithium battery pack, a power distribution module, a flight control motherboard, an IMU sensor, and a wireless communication module. The lithium battery pack, power distribution module, flight control motherboard, IMU sensor, and wireless communication module are respectively mounted on multiple support plates 14. The lithium battery pack is electrically connected to the power distribution module. The multiple output motors 232, the flight control motherboard, the IMU sensor, and the wireless communication module are respectively electrically connected to the power distribution module. The flight control motherboard is electrically connected to the IMU sensor, the flight control motherboard is electrically connected to the wireless communication module, and the flight control motherboard is electrically connected to the multiple output motors 232.

[0036] The working principle and beneficial effects of the above technical solution are as follows: The flight control motherboard is independently connected to multiple output motors 232 with electrical signals. When a single output motor 232 malfunctions, the flight control motherboard controls the remaining output motors 232 to adjust the lift to ensure the stability of the UAV. Multiple support plates 14 support and fix the lithium battery pack, power distribution module, flight control motherboard, IMU sensor and wireless communication module respectively. The layered electrical architecture and distributed power supply reduce line loss. The lithium battery pack and power distribution module form a power bus. The flight control motherboard obtains attitude data through the IMU, calculates it with a PID algorithm, and outputs PWM control signals to each motor.

[0037] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this application.

Claims

1. An octocopter unmanned aerial vehicle (UAV), characterized in that: It includes a fuselage mechanism (1), a rotor mechanism (2) and a control system. The rotor mechanism (2) is located on the periphery of the fuselage mechanism (1), the control system is located inside the fuselage mechanism (1), and a cargo carrier mechanism (3) is located at the bottom of the fuselage mechanism (1).

2. An octocopter UAV according to claim 1, characterized in that: The fuselage mechanism (1) includes a horizontally arranged top plate (11) and bottom plate (12). The top plate (11) and the bottom plate (12) are connected by a plurality of vertically arranged fixed columns (13). A plurality of support plates (14) are horizontally arranged on the fixed columns (13) between the top plate (11) and the bottom plate (12). Protective plates (15) and heat dissipation plates (16) are respectively arranged around the top plate (11) and the bottom plate (12). The protective plates (15) and the heat dissipation plates (16) are respectively connected to the fixed columns (13) by fasteners (17).

3. An octocopter UAV according to claim 2, characterized in that: The rotor mechanism (2) includes a limiting plate (21), which is set on the top of the plurality of fixed columns (13) and fixedly connected to the bottom of the top plate (11). Support arms (22) are fixedly set at the four corners of the limiting plate (21). Take-off and landing components (23) are fixedly set on the upper and lower sides of the middle part of the support arm (22). The take-off and landing components (23) include a stabilizing plate (231), which is set on the support arm (22). An output motor (232) is fixedly set on the stabilizing plate (231). The output end of the output motor (232) is driven by a lifting blade (233). Two buffer pads (234) are symmetrically arranged between the stabilizing plate (231) and the support arm (22).

4. An octocopter UAV according to claim 3, characterized in that: The other ends of the multiple support arms (22) are respectively fixedly connected to the first fixing ring (235). Multiple slots (236) are provided on the support arms (22). A second fixing ring (237) perpendicular to the first fixing ring (235) is fitted into each slot (236). A first locking element (238) is fitted at the connection between the first fixing ring (235) and the second fixing ring (237). A first curved groove (239) is provided on the first fixing ring (235). The first bend (239) is engaged with the second bend (242) on the third fixing ring (241) by a snap-fit ​​connector (240). The top ends of the second fixing ring (237) and the third fixing ring (241) are fixedly connected by a first adapter (243). A clamping plate (244) is fixedly provided at the bottom of the base plate (12). The bottom ends of the second fixing ring (237) and the third fixing ring (241) are located between the base plate (12) and the clamping plate (244).

5. An octocopter UAV according to claim 4, characterized in that: The latch (240) includes a second latch (2401), which is latched at the intersection of the first groove (239) and the second groove (242) and fixed by bolts. A balance plate (2403) is fixedly provided on the side of the second latch (2401) away from the body mechanism (1), and a balance block (2402) is provided on the outside of the balance plate (2403).

6. An octocopter UAV according to claim 4, characterized in that: The first adapter (243) includes a first locking plate (2431) and a second locking plate (2432). The first locking plate (2431) and the second locking plate (2432) are respectively fixedly disposed on the upper and lower sides of the top of the second fixing ring (237) and the third fixing ring (241). The top of the first locking plate (2431) is fixedly disposed with a cover plate (2433) by bolts.

7. An octocopter UAV according to claim 2, characterized in that: The loading mechanism (3) includes a load plate (31), which is bolted to the bottom of the base plate (12), and a loading box (32) is fixedly installed below the load plate (31).

8. An octocopter UAV according to claim 3, characterized in that: The control system includes a lithium battery pack, a power distribution module, a flight control motherboard, an IMU sensor, and a wireless communication module. The lithium battery pack, power distribution module, flight control motherboard, IMU sensor, and wireless communication module are respectively mounted on multiple support plates (14). The lithium battery pack is electrically connected to the power distribution module. The multiple output motors (232), flight control motherboard, IMU sensor, and wireless communication module are respectively electrically connected to the power distribution module. The flight control motherboard is electrically connected to the IMU sensor, the flight control motherboard is electrically connected to the wireless communication module, and the flight control motherboard is electrically connected to the multiple output motors (232).

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