Folding multi-rotor unmanned aerial vehicle

Abstract

The utility model discloses a folding multi-rotor unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, the folding multi-rotor unmanned aerial vehicle comprises a battery cabin, a frame body supporting rod, a frame body and a vehicle body, the vehicle body is fixedly installed on the outer side of the upper surface of the battery cabin, and a top cover is arranged at the top end of the vehicle body; the frame body supporting rod is fixedly installed in the middle of the upper surface of the battery cabin, and a rolling ball, a protruding block, a spring and a spherical rod are arranged and matched with a spherical limiting groove formed in the tail end of the rotating frame, so that when the unmanned aerial vehicle is launched in the launching sleeve and accelerated in the sleeve, the wings are always fixed into the fuselage, and therefore the unmanned aerial vehicle is more stable. When the wings completely leave the sleeve, the clamping device can automatically release fixation of the wings, so that the wings are unfolded and flight operation is completed, friction between a flight structure and the inner wall of the launching cylinder in the launching process of the unmanned aerial vehicle can be effectively avoided, and the problem that important assemblies are abraded in the launching process is solved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a foldable multi-rotor unmanned aerial vehicle. Background Art

[0002] The currently published patent: CN202221794061.6 discloses a folding multi-rotor UAV, including a fuselage, a mounting frame and a plurality of wing-spreading rotor modules. The shape of the fuselage is barrel-shaped, so that the fuselage can be loaded into the bomb body for launch, the mounting frame is arranged in the fuselage, and the side wall of the fuselage is circumferentially spaced with a plurality of storage slots, each of which extends along the length direction of the fuselage. Multiple wing-spreading rotor modules are arranged in a one-to-one correspondence in a plurality of storage slots, and the ends of each wing-spreading rotor module are hinged to the mounting frame so that the wing-spreading rotor module can be expanded outward from the storage slot, thereby increasing the endurance time of the UAV to perform the mission after reaching the destination.

[0003] However, the following problems may occur during the use of this solution: the rotating frame in the above-mentioned prior art may produce friction with the inner wall of the launch tube during the launch of the UAV, causing wear of the launch component, thereby affecting subsequent use. Utility Model Content

[0004] 1. Technical issues to be resolved

[0005] The purpose of the utility model is to solve at least one of the technical problems existing in the prior art and to provide a foldable multi-rotor UAV which can solve the problem in the prior art that the UAV will generate friction with the inner wall of the launch tube during the launch process, causing wear of the launch assembly and thus affecting subsequent use.

[0006] (II) Technical solution

[0007] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0008] A folding multi-rotor drone comprises a battery compartment, a frame support rod, a frame and a fuselage, wherein the fuselage is fixedly mounted on the outer side of the upper surface of the battery compartment, a top cover is arranged on the top of the fuselage, the frame support rod is fixedly mounted on the middle position of the upper surface of the battery compartment, the frame is fixedly mounted on the top of the frame support rod, a flight control module is fixedly mounted on the top of the frame, the top of the flight control module is fitted with the lower end surface of the top cover, and the characteristic is that four folding devices are evenly arranged around the frame;

[0009] Each folding device includes two mounting plates, which are fixedly mounted on the outer surface of the frame body, a rotating frame is arranged between the two mounting plates, a motor is fixedly mounted on the upper surface of one end of the rotating frame away from the mounting plates, the output shaft of the motor rotates and penetrates the lower surface of the rotating frame, a propeller hub is fixedly mounted on the output pump of the motor, and two propeller blades are installed at the bottom end of the propeller hub;

[0010] Among them, support plates are fixedly installed around the bottom end of the frame support rod, and cross grooves are opened on the four support plates. The inside of the four cross grooves are provided with clamping devices, which are used to clamp the corresponding rotating frame inside the fuselage.

[0011] Preferably, arc-shaped mounting holes and pin holes are provided on the opposite surfaces of the two corresponding mounting plates, a first pin shaft is rotatably inserted inside the two corresponding pin holes, a second pin shaft is rotatably inserted inside the two corresponding arc-shaped mounting holes, the tail end of the rotating frame is fixedly connected to the second pin shaft, and the rotating frame is rotatably connected to the first pin shaft.

[0012] Preferably, a support rod is fixedly installed between the two corresponding mounting plates, a torsion spring is rotatably sleeved on the outer surface of the support rod, a T-shaped block is fixedly installed on one end of the torsion spring, the end of the T-shaped block away from the torsion spring is fixedly installed on the corresponding rotating frame, and a fixing plate is fixedly installed on the other end of the torsion spring, and the fixing plate is fixedly connected to the mounting plate.

[0013] Preferably, the clamping device comprises four spherical stop grooves on one end of the rotating frame away from the frame body;

[0014] Among them, hollow sleeves are fixedly installed on the outer surface of the frame support rod corresponding to the upper positions of the four protrusions, and spherical rods are slidably inserted on the four hollow sleeves.

[0015] The cross slider is slidably installed inside the corresponding cross groove. A protrusion is fixedly installed on the upper surface of the cross slider, and an inclined groove is arranged on the upper surface of the protrusion.

[0016] The bottom ends of the four spherical rods are all extended to the oblique grooves of the corresponding protrusions, and the sizes of the top spheres of the four spherical rods are adapted to the corresponding spherical limiting grooves.

[0017] Preferably, a spring is fixedly installed at a position on the outer surface of the frame support rod corresponding to the protrusion, and one end of the spring away from the frame support rod is fixedly connected to the protrusion.

[0018] Preferably, a rolling ball is movably embedded on one side of the protrusion away from the frame support rod.

[0019] (III) Beneficial effects

[0020] Compared with the prior art, the beneficial effects of the utility model are:

[0021] (1) The foldable multi-rotor UAV is provided with a rolling ball, a bump, a spring and a spherical rod, and cooperates with a spherical limit groove provided at the end of the rotating frame, so that when the UAV is launched in the launch sleeve and accelerated in the sleeve, the wings are always fixed inside the fuselage. When the wings completely leave the sleeve, the clamping device can automatically release the fixation of the wings, so that the wings can be unfolded and the flight operation can be completed. The friction between the flight structure of the UAV and the inner wall of the launch tube during the launch process can be effectively avoided, and the problem of wear of important components during the launch process is solved.

[0022] (2) The foldable multi-rotor drone has an inclined groove on the upper surface of the protrusion to facilitate the upward movement of the spherical rod, thereby enabling the spherical rod to engage with the corresponding spherical limit groove. In addition, a rolling ball is arranged on the outer side of the protrusion so that the rolling ball contacts the inner wall of the launch tube during the launching and storage process, thereby further preventing the inner wall of the launch tube from being worn. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The utility model is further described below in conjunction with the accompanying drawings and embodiments:

[0024] Figure 1 This is a schematic diagram of the overall structure of a foldable multi-rotor drone of the utility model;

[0025] Figure 2 It is a schematic diagram of the overall cross-sectional view of the utility model;

[0026] Figure 3 This is a structural diagram of a single wing of the utility model;

[0027] Figure 4 This is a schematic diagram of the frame structure of the utility model;

[0028] Figure 5 It is a schematic diagram of the clamping device of the utility model.

[0029] Figure numerals: 1. battery compartment; 2. cross slider; 3. cross groove; 4. rolling ball; 5. bump; 6. hollow sleeve; 7. spherical rod; 8. support plate; 9. blade; 10. motor; 11. top cover; 12. fuselage; 13. spherical limit groove; 14. torsion spring; 15. flight control module; 16. arc-shaped mounting hole; 17. frame; 18. first pin shaft; 19. second pin shaft; 20. spring; 21. frame support rod; 22. support rod; 23. T-shaped block; 24. fixing plate; 25. second support plate; 26. rotating frame; 27. propeller hub; 28. pin hole; 29. ​​mounting plate. DETAILED DESCRIPTION

[0030] This section will describe in detail the specific embodiments of the utility model. The preferred embodiments of the utility model are shown in the accompanying drawings. The purpose of the accompanying drawings is to supplement the description of the text part of the specification with graphics, so that people can intuitively and vividly understand each technical feature and the overall technical solution of the utility model, but it cannot be understood as a limitation on the protection scope of the utility model.

[0031] The utility model provides a technical solution: please refer to Figure 1-2 A foldable multi-rotor drone comprises a battery compartment 1, a frame support rod 21, a frame 17 and a fuselage 12. The fuselage 12 is cylindrical, and storage slots for storing a rotating frame 26 are provided on all sides of the fuselage 12. The fuselage 12 is fixedly mounted on the outer side of the upper surface of the battery compartment 1, and a top cover 11 is fixedly mounted on the top of the fuselage 12. The frame support rod 21 is fixedly mounted in the middle position of the upper surface of the battery compartment 1, and a frame 17 is fixedly mounted on the top of the frame support rod 21. A flight control module 15 is fixedly mounted on the top of the frame 17, and the flight control module 15 is tightly fitted with the top cover 11. The fuselage 12 is sleeved on the outer side of the frame support rod 21, the frame 17 and the flight control module 15. The flight control module 15 is used to control the start and stop of the motor.

[0032] Specifically, four folding devices are evenly arranged around the frame 17. Figure 4 As shown. Each folding device includes two mounting plates 29, and the two mounting plates 29 are fixedly mounted on the outer surface of the frame 17. A rotating frame 26 is arranged between the two mounting plates 29. A motor 10 is fixedly mounted on the upper surface of the rotating frame 26 at one end away from the mounting plate 29. The output shaft of the motor 10 rotates and penetrates the lower surface of the rotating frame 26. A hub 27 is fixedly mounted on the output pump of the motor 10, and two blades 9 are installed at the bottom end of the hub 27. The rotation of the motor 10 drives the hub 27 to rotate synchronously, and the rotation of the hub 27 drives the two blades 9 to rotate. The blades 9 can be folded and stored in the fuselage 12. The blades 9 and the hub 27 are connected by a rotating and unfolding assembly. The rotating and unfolding assembly belongs to the prior art and will not be described here.

[0033] Further, such as Figure 3 As shown, support plates 8 are fixedly installed around the bottom end of the frame support rod 21, and four support plates 8 are provided with cross grooves 3. The inside of the four cross grooves 3 is provided with a clamping device, which is used to automatically clamp the corresponding rotating frame 26 inside the fuselage 12.

[0034] It should be noted that if Figure 4 As shown, the two corresponding mounting plates 29 have arc-shaped mounting holes 16 and pin holes 28 on their opposite surfaces. Figure 3As shown, the first pin shaft 18 is rotatably inserted in the two corresponding pin holes 28, the second pin shaft 19 is rotatably inserted in the two corresponding arc-shaped mounting holes 16, the tail end of the rotating frame 26 is fixedly connected to the second pin shaft 19, and the rotating frame 26 is rotatably connected to the first pin shaft 18.

[0035] Further, such as Figure 2 As shown, a support rod 22 is fixedly installed between two corresponding mounting plates 29, and a torsion spring 14 is rotatably sleeved on the outer surface of the support rod 22. A T-shaped block 23 is fixedly installed at one end of the torsion spring 14, and the end of the T-shaped block 23 away from the torsion spring 14 is fixedly installed on the corresponding rotating frame 26. A fixed plate 24 is fixedly installed at the other end of the torsion spring 14, and the fixed plate 24 is fixedly connected to the corresponding mounting plate 29. A downward force is applied to the rotating frame 26, and the rotating frame 26 rotates around the first pin shaft 18, and cooperates with the sliding of the second pin shaft 19 in the arc-shaped mounting hole 16 to complete the folding action of the rotating frame 26. The folding of the rotating frame 26 drives the torsion spring 14 to start elastic deformation through the fixed plate 24 and the T-shaped block 23. At this time, the torsion spring 14 is in a deformed and force-accumulating state.

[0036] Further, such as Figure 5 As shown, the clamping device includes a cross slider 2, which is slidably mounted inside the corresponding cross groove 3, and a protrusion 5 is fixedly mounted on the upper surface of the cross slider 2, and a ball 4 is rotatably inserted on the side of the protrusion 5 away from the frame support rod 21;

[0037] Among them, a spring 20 is fixedly installed on the position of the outer surface of the frame support rod 21 corresponding to the protrusion 5, and the end of the spring 20 away from the frame support rod 21 is fixedly connected to the protrusion 5. The fuselage 12 is placed in the launching tube, and the ball 4 slides along the inner wall of the launching tube. The cross slider 2 fixed under the protrusion 5 moves toward the inside of the fuselage 12 along the cross groove 3, the protrusion 5 shrinks inward, and the spherical rod 7 moves upward along the hollow sleeve 6. When the raised upper surface of the protrusion 5 contacts the lower surface of the spherical rod 7, the upper end of the spherical rod 7 moves just into the spherical limit groove 13. At this time, the spring 20 fixed to the protrusion 5 is compressed, and the ball 4 presses against the inner wall of the launching tube under the action of the spring 20, and the rotating frame 26 is fixed inside the fuselage 12.

[0038] Further, such as Figure 3 As shown, the upper surface of the projection 5 is provided with an inclined groove for pushing the spherical rod 7 upward.

[0039] It should be noted that if Figure 3 As shown, the ends of the four rotating frames 26 away from the frame body 17 are all provided with spherical limiting grooves 13;

[0040] Among them, hollow sleeves 6 are fixedly installed on the outer surface of the frame support rod 21 at the upper positions corresponding to the four protrusions 5, and spherical rods 7 are slidably inserted on the four hollow sleeves 6. The bottom ends of the four spherical rods 7 extend to the oblique grooves of the corresponding protrusions 5, and the size of the top spheres of the four spherical rods 7 is adapted to the corresponding spherical limit grooves 13.

[0041] When the fuselage 12 is launched from the launch tube, the fuselage 12 moves upward along the inner wall of the launch tube. When the rotating frame 26 completely leaves the launch tube and the ball 4 on the protrusion 5 is not completely separated from the inner wall of the launch tube, the rotating frame 26 is still limited inside the fuselage 12. When the ball 4 on the protrusion 5 is completely out of contact with the inner wall of the launch tube, the spring 20 pushes the protrusion 5 to move toward the outside of the fuselage 12 along the cross groove 3 under the action of elastic deformation. The spherical rod 7 moves downward along the hollow sleeve 6 under the action of gravity. When the lower surface of the spherical rod 7 contacts the lowest point of the protrusion 5, the upper end of the spherical rod 7 is separated from the spherical limiting groove 13. Under the action of the torsion spring 14, the rotating frame 26 rotates around the first pin 18 and unfolds with the cooperation of the second pin 19 in the arc-shaped mounting hole 16. The motor 10 rotates under the control of the flight control module 15 to achieve flight operations.

[0042] Working principle: First, rotate the two blades 9 on the corresponding propeller hub 27 so that the two blades 9 are folded inwardly to be parallel to the rotating frame 26. Apply a downward force to the rotating frame 26, the rotating frame 26 rotates around the first pin 18, and cooperates with the sliding of the second pin 19 in the arc-shaped mounting hole 16 to complete the folding action of the rotating frame 26. At this time, the torsion spring 14 is in a deformed and stored state, the fuselage 12 is placed in the launch tube, the ball 4 slides along the inner wall of the launch tube, the cross slider 2 fixed under the protrusion 5 moves along the cross groove 3 to the inside of the fuselage 12, and the protrusion 5 shrinks inward. The spherical rod 7 moves upward along the hollow sleeve 6, and when the raised upper surface of the protrusion 5 contacts the lower surface of the spherical rod 7, the upper end of the spherical rod 7 just moves into the spherical limit groove 13. At this time, the spring 20 fixed to the protrusion 5 is compressed, and the ball 4 presses against the inner wall of the launch tube under the action of the spring 20, and the rotating frame 26 is fixed inside the fuselage 12.

[0043] When the fuselage 12 is launched from the launch tube, the fuselage 12 moves upward along the inner wall of the launch tube. When the rotating frame 26 completely leaves the launch tube and the ball 4 on the protrusion 5 is not completely separated from the inner wall of the launch tube, the rotating frame 26 is still fixed inside the fuselage 12.

[0044] When the ball 4 on the bump 5 is completely out of contact with the inner wall of the launch tube, the spring 20 pushes the bump 5 to move along the cross groove 3 toward the outside of the fuselage 12 under the action of elastic deformation. The spherical rod 7 moves downward along the hollow sleeve 6 under the action of gravity. When the lower surface of the spherical rod 7 contacts the lowest point of the bump 5, the upper end of the spherical rod 7 is disengaged from the spherical limit groove 13. Under the action of the torsion spring 14, the rotating frame 26 rotates around the first pin 18 and unfolds under the cooperation of the second pin 19 and the arc-shaped mounting hole 16. The motor 10 rotates under the control of the flight control module 15, and then unfolds the blades 9 to achieve flight operations.

[0045] The embodiments of the present invention are described in detail above in conjunction with the accompanying drawings, but the present invention is not limited to the above embodiments. Various changes can be made within the knowledge scope of ordinary technicians in the technical field without departing from the purpose of the present invention.

Claims

1. A folding multi-rotor drone, comprising a battery compartment (1), a frame support rod (21), a frame (17) and a fuselage (12), wherein the fuselage (12) is fixedly mounted on the outer side of the upper surface of the battery compartment (1), a top cover (11) is arranged at the top of the fuselage (12), the frame support rod (21) is fixedly mounted at the middle position of the upper surface of the battery compartment (1), the frame (17) is fixedly mounted on the top of the frame support rod (21), a flight control module (15) is fixedly mounted on the top of the frame (17), the top of the flight control module (15) is in contact with the lower end surface of the top cover (11), and the characteristics are as follows: Four folding devices are evenly arranged around the frame (17); Each folding device comprises two mounting plates (29), the two mounting plates (29) are fixedly mounted on the outer surface of the frame body (17), a rotating frame (26) is arranged between the two mounting plates (29), a motor (10) is fixedly mounted on the upper surface of one end of the rotating frame (26) away from the mounting plates (29), an output shaft of the motor (10) rotates and penetrates the lower surface of the rotating frame (26), a propeller hub (27) is fixedly mounted on the output pump of the motor (10), and two propeller blades (9) are mounted on the bottom end of the propeller hub (27); Wherein, support plates (8) are fixedly installed around the bottom end of the frame support rod (21), four support plates (8) are provided with cross grooves (3), and the inside of the four cross grooves (3) are provided with a clamping device, which is used to clamp the corresponding rotating frame (26) inside the fuselage (12); The clamping device comprises four rotating frames (26) each having a spherical limiting groove (13) at one end away from the frame body (17); Wherein, hollow sleeves (6) are fixedly installed on the outer surface of the frame support rod (21) at positions above the four protrusions (5), and spherical rods (7) are slidably inserted into the four hollow sleeves (6). A cross slider (2) is slidably mounted inside the corresponding cross groove (3), a protrusion (5) is fixedly mounted on the upper surface of the cross slider (2), and an oblique groove is provided on the upper surface of the protrusion (5). The bottom ends of the four spherical rods (7) extend to the oblique grooves of the corresponding protrusions (5), and the sizes of the top spheres of the four spherical rods (7) match the corresponding spherical limiting grooves (13); A rolling ball (4) is movably embedded on one side of the protrusion (5) away from the frame support rod (21).

2. A foldable multi-rotor drone according to claim 1, characterized in that: The two corresponding mounting plates (29) are provided with arc-shaped mounting holes (16) and pin holes (28) on their opposite surfaces; the first pin shafts (18) are rotatably inserted in the two corresponding pin holes (28); the second pin shafts (19) are rotatably inserted in the two corresponding arc-shaped mounting holes (16); the rear end of the rotating frame (26) is fixedly connected to the second pin shaft (19); and the rotating frame (26) is rotatably connected to the first pin shaft (18).

3. A foldable multi-rotor drone according to claim 2, characterized in that: A support rod (22) is fixedly mounted between the two corresponding mounting plates (29), a torsion spring (14) is rotatably sleeved on the outer surface of the support rod (22), a T-shaped block (23) is fixedly mounted on one end of the torsion spring (14), an end of the T-shaped block (23) away from the torsion spring (14) is fixedly mounted on the corresponding rotating frame (26), a fixing plate (24) is fixedly mounted on the other end of the torsion spring (14), and the fixing plate (24) is fixedly connected to the mounting plate (29).

4. The foldable multi-rotor drone according to claim 1, characterized in that: A spring (20) is fixedly mounted on the outer surface of the frame support rod (21) at a position corresponding to the protrusion (5), and one end of the spring (20) away from the frame support rod (21) is fixedly connected to the protrusion (5).

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