Eight-shaft multi-rotor heavy-load unmanned aerial vehicle

Abstract

The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle rotor arm structure eight-shaft multi-rotor heavy-load unmanned aerial vehicle which comprises a vehicle body, a cover plate is arranged at the top of the vehicle body, eight foldable rotor arms are arranged on the periphery of the vehicle body, motors are installed at the far ends of the rotor arms, and main pipe clamps are installed at the near ends of the rotor arms; the main pipe clamp comprises an enclasping part and an end plate, the enclasping part comprises a left half hoop body and a right half hoop body, arc-shaped surfaces of the left half hoop body and the right half hoop body form a circular enclasping clamping hole, extending bodies are arranged at the upper ends of the left half hoop body and the right half hoop body, and first fastening holes are formed in the two extending bodies; the number of the end plates is two, the end plates are located on the two sides of the enclasping part respectively, the end plates and the left half hoop body are integrally formed, and gaps are reserved between the end plates and the right half hoop body. First mounting holes are formed in the upper and lower ends of the end plates. The eight-shaft multi-rotor heavy-load unmanned aerial vehicle is better in stability, the rotor arms and the vehicle body are connected more firmly, and heavy-load flight of the unmanned aerial vehicle is facilitated.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicles (UAVs), and more particularly to an octagonal multi-rotor heavy-duty UAV. Background Technology

[0002] In the era of rapid development of the drone industry, special-purpose drones have gradually come into the public eye. Among them, heavy-duty drones are widely used in fields such as express delivery and fire rescue due to their large payload capacity. The rotor arm of the drone plays a very important role in the flight process as a key component of heavy-duty drones.

[0003] like Figure 1 The image shows a rotor arm mounting structure for a conventional heavy-duty UAV. The rotor arm is typically a carbon fiber tube, often referred to as a carbon tube. Its proximal end is usually fixed to the UAV fuselage using a C-shaped clamp. Due to dimensional tolerances in the carbon tube, the upper and lower end faces of the C-shaped clamp are not horizontal after clamping the carbon tube. The upper and lower end faces of the clamp cannot be directly fitted and fixed to the fuselage (leaving a gap between them), resulting in insufficient stability of the UAV rotor arm. Summary of the Invention

[0004] Based on the above problems, the purpose of this invention is to provide an eight-rotor heavy-duty unmanned aerial vehicle (UAV). The invention adopts the following technical solution: This invention provides an eight-rotor heavy-duty unmanned aerial vehicle (UAV), including a fuselage, a cover plate on the top of the fuselage, eight foldable rotor arms arranged around the fuselage, a motor mount mounted on the distal end of each rotor arm, a motor mounted on the motor mount, a propeller mounted on the drive shaft of the motor, and multiple main clamps mounted on the proximal end of each rotor arm. The top of each main clamp is connected to the cover plate and the top of each main clamp is connected to the fuselage. The main clamp includes a clamping part and end plates. The clamping part includes a left half-hoop and a right half-hoop, the lower ends of which are integrally formed. The left and right half-hoops are symmetrically arranged, and their arc surfaces form a circular clamping hole. A gap is left at the upper ends of the left and right half-hoops, and an extension is provided at the upper ends of both the left and right half-hoops. Each extension has a first fastening hole. There are two end plates, located on both sides of the clamping part. A through hole is provided on the end plate corresponding to the position of the circular clamping hole, and the diameter of the through hole is the same as the diameter of the circular clamping hole. The end plate is integrally formed with the left half-hoop, and a gap is left between the end plate and the right half-hoop. First mounting holes are provided at both the upper and lower ends of the end plate.

[0005] Preferably, a secondary tube clamp is installed at the proximal end of the rotor arm, the secondary tube clamp being located between two adjacent main tube clamps, and the secondary tube clamp comprising two clamping bodies arranged symmetrically; The clamp includes an arc-shaped segment with an opening facing the side, and horizontal segments are provided at both the upper and lower positions of the arc-shaped segment. The horizontal segments are connected to the arc-shaped segment through vertical segments. A bent segment is provided at one end of the horizontal segment on the same side as the opening of the arc-shaped segment. The bent segment extends toward the opening of the arc-shaped segment, and a vertically arranged connecting segment is provided at the extended end of the bent segment. A second mounting hole is provided on the horizontal section; a second fastening hole is provided on both the docking section and the vertical section, and the two second fastening holes are arranged on the same axis.

[0006] Preferably, the end plate is provided with a plurality of perforated holes; the perforated holes are elongated and extend in the vertical direction. Preferably, both the upper and lower ends of the end plate are provided with laterally extending feet, and the first mounting hole is provided on the feet.

[0007] Preferably, threaded holes are provided on both the left and right side walls of the end plate.

[0008] Preferably, the rotor arm includes a fixed arm and a movable arm, which are connected by a folding member.

[0009] Preferably, the folding component includes a first sleeve and a second sleeve with a cross-shaped notch on their outer walls, and a third fastening hole is provided on both sides of the corresponding cross-shaped notch on the outer walls of the first sleeve and the second sleeve. The first and second jackets are respectively fixed with a first fixing plate and a second fixing plate at their adjacent ends. The top of the first fixing plate is provided with a connecting groove, and the top of the second fixing plate is provided with a connecting platform. The connecting platform is rotatably connected to the connecting groove. The bottoms of the first and second fixing plates are fixed by bolts.

[0010] Preferably, the bottom of the machine body is provided with a tripod, and a searchlight is provided on the tripod.

[0011] Preferably, a camera and radar are provided on the side of the fuselage.

[0012] Preferably, the body has multiple sunken battery compartments, and the cover plate has battery insertion holes corresponding to the positions of the battery compartments.

[0013] Preferably, the motor base includes a base body symmetrically arranged on the horizontal plane, and each of the mating surfaces of the two base bodies is provided with a groove for clamping and engaging with the arm body. Each side of the base body is provided with a foot plate, and the foot plate is provided with a mounting hole. Each base body is provided with a connecting seat on the side facing away from the groove, and the motor is mounted on the connecting seat.

[0014] Compared with the prior art, the beneficial technical effects of the present invention are as follows: The eight-rotor heavy-load UAV of the present invention has better stability and a more secure connection between the rotor arms and the fuselage, which is conducive to the heavy-load flight of the UAV. Attached Figure Description

[0015] The present invention will be further described below with reference to the accompanying drawings.

[0016] Figure 1 A schematic diagram of the rotor arm installation structure of an existing heavy-duty UAV; Figure 2 This is a schematic diagram of the structure of the eight-axis multi-rotor heavy-duty UAV of the present invention; Figure 3 This is a schematic diagram of the structure of the rotor arm of the UAV of the present invention; Figure 4 This is a schematic diagram of the main clamp state of the present invention; Figure 5 This is a schematic diagram of the second state of the main clamp of the present invention; Figure 6 This is a schematic diagram of the main clamp state three of the present invention; Figure 7 This is a schematic cross-sectional view of the main clamp structure of the present invention; Figure 8 This is a schematic diagram of the secondary pipe clamp of the present invention; Figure 9 This is a schematic diagram of the structure of the clamp body of the present invention; Figure 10 This is a schematic diagram of the structure of the folding component of the present invention; Figure 11 This is a schematic diagram of the structure of the first jacket of the present invention; Figure 12 This is a schematic diagram of the structure of the second jacket of the present invention; Figure 13 This is a schematic diagram of the battery compartment arrangement on the body of the present invention; Figure 14 This is a schematic diagram of the cover plate of the present invention; Figure 15 This is a schematic diagram of the motor base and arm mounting structure of the present invention; Figure 16 This is a schematic diagram of the structure of the base (non-groove side) of the present invention; Figure 17This is a schematic diagram of the structure of the base (groove side) of the present invention.

[0017] Explanation of reference numerals in the attached drawings: 1. Rotor arm; 101. Fixed arm; 102. Movable arm; 2. Main clamp; 201. Clamping part; 201-1. Left half of the hoop; 201-2. Right half of the hoop; 201-3. Circular clamping hole; 201-4. Extension body; 201-5. First fastening hole; 202. End plate; 202-1. Through hole; 202-2. First mounting hole; 202-3. Hollow hole; 202-4. Support leg; 202-5. Threaded hole; 3. Secondary pipe clamp; 301. Clamp body; 301-1. Arc-shaped section; 301-2. Horizontal section; 301-3. Vertical section; 301-4. 301-5. Bending section; 301-6. Second mounting hole; 301-7. Second fastening hole; 4. Motor base; 401. Base body; 402. Groove; 403. Foot plate; 404. Connecting seat; 5. Motor; 6. Propeller blade; 7. Folding part; 701. First sleeve; 702. Second sleeve; 703. Third fastening hole; 704. First fixing plate; 705. Second fixing plate; 706. Connecting groove; 707. Connecting platform; 8. Fuselage; 801. Cover plate; 802. Battery insertion hole; 9. Tripod; 10. Searchlight; 11. Camera; 12. Radar; 13. Battery compartment; Detailed Implementation

[0018] To make the technical problems, technical solutions, and beneficial effects of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments.

[0019] like Figure 2 and 3 As shown, this embodiment discloses an eight-rotor heavy-duty unmanned aerial vehicle (UAV), including a fuselage 8. A cover plate 801 is bolted to the top of the fuselage 8. Eight foldable rotor arms 1 (rotor arms 1 are typically carbon fiber tubes, also known as carbon tubes) are arranged around the fuselage 8. A motor mount 4 is installed at the far end of each rotor arm 1, and a motor 5 is installed on the motor mount 4. A propeller 6 is installed on the drive shaft of the motor 5. Multiple main tube clamps 2 are installed at the near end of each rotor arm 1. The top of the main tube clamp 2 is connected to the cover plate 801, and the top of the main tube clamp 2 is connected to the fuselage 8.

[0020] like Figures 4 to 7As shown, the main clamp 2 includes a clamping part 201 and an end plate 202. The clamping part 201 includes a left half-hoop 201-1 and a right half-hoop 201-2. The lower ends of the left half-hoop 201-1 and the right half-hoop 201-2 are integrally formed. The left half-hoop 201-1 and the right half-hoop 201-2 are arranged symmetrically, and their arc surfaces form a circular clamping hole 201-3. There is a gap between the upper ends of the left half-hoop 201-1 and the right half-hoop 201-2, and an extension 201-4 is provided at the upper end of both the left half-hoop 201-1 and the right half-hoop 201-2. Each of the two extensions 201-4 is provided with a first fastening hole 201-5. The clamping part 201 clamps the rotor arm 1 by fastening the first fastening holes 201-5 on the two extensions 201-4 with bolt assemblies.

[0021] There are two end plates 202, located on both sides of the clamping part 201. A through hole 202-1 is provided on each end plate 202 at the position corresponding to the circular clamping hole 201-3. The diameter of the through hole 202-1 is the same as the diameter of the circular clamping hole 201-3. The end plate 202 is integrally formed with the left half of the hoop 201-1, and a gap is left between the end plate 202 and the right half of the hoop 201-2. First mounting holes 202-2 are provided at both the top and bottom of the end plate 202. The first mounting hole 202-2 at the top is connected to the cover plate 801 by bolts, and the first mounting hole 202-2 at the bottom is connected to the machine body 8 by bolts.

[0022] Compared to existing pipe clamps, the clamping method of the main pipe clamp 2 has been changed from the original one-sided clamping to the current top clamping, which has lower requirements for the outer diameter deviation of the carbon pipe. At the same time, the first mounting hole 202-2 for installation and fixing with the UAV cover plate 801 and fuselage 8 is designed at the upper and lower ends of the end plate 202. During installation and fixing, it is not affected by the clamping part 201. The upper and lower end faces of the main pipe clamp 2 can better fit and fix with the fuselage shell, making the rotor arm structure installation more stable.

[0023] In this embodiment, the end plate 202 is provided with a plurality of hollow holes 202-3; the hollow holes 202-3 are elongated and extend along the vertical direction to reduce the overall weight of the pipe clamp.

[0024] In this embodiment, both the upper and lower ends of the end plate 202 are provided with laterally extending support legs 202-4, and the first mounting hole 202-2 is provided on the support legs 202-4.

[0025] In this embodiment, threaded holes 202-5 are provided on both the left and right side walls of the end plate 202, and the threaded holes 202-5 are connected to the through holes 202-1. After the rotor arm 1 is installed on the main clamp 2, a set screw is installed in the threaded hole 205 to tighten the set screw on the rotor arm 1, thereby improving the torsional resistance of the rotor arm 1.

[0026] like Figure 8 and 9 As shown, a secondary tube clamp 3 is installed at the near end of the rotor arm 1, and the secondary tube clamp 3 is located between the two main tube clamps 2. The secondary tube clamp 3 includes two clamp bodies 301 arranged symmetrically, each clamp body 301 is an integral structure, and the clamp body 301 can be made of aluminum alloy.

[0027] The clamp 301 includes an arc-shaped segment 301-1 with its opening facing the side. Horizontal segments 301-2 are provided at both the upper and lower positions of the arc-shaped segment 301-1. The horizontal segments 301-2 are connected to the arc-shaped segment 301-1 through a vertical segment 301-3. A bent segment 301-4 is provided at one end of the horizontal segment 301-2 on the same side as the opening of the arc-shaped segment 301-1. The bent segment 301-4 extends toward the opening side of the arc-shaped segment 301-1, and a vertically arranged butt joint segment 301-5 is provided at the extended end of the bent segment 301-4.

[0028] A second mounting hole 301-6 is provided on the horizontal section 301-2; the second mounting hole 301-6 is located closer to the end of the horizontal section 301-2 away from the arc section 301-1. The second mounting hole 301-6 located at the top is connected to the cover plate 801 by bolts, and the second mounting hole 301-6 located at the bottom is connected to the machine body 8 by bolts.

[0029] A second fastening hole 301-7 is provided on both the docking section 301-5 and the vertical section 301-3, and the two second fastening holes 301-7 are arranged coaxially. Two clamping bodies 301 are symmetrically arranged on both sides of the rotor arm 1, and the two clamping bodies 301 are clamped on the rotor arm 1 after the bolt assembly passes through the second fastening hole 301-7.

[0030] like Figures 10 to 12 As shown, the rotor arm 1 includes a fixed arm 101 and a movable arm 102, which are connected by a folding member 7. In this embodiment, the fixed arm 101 is fixed in the UAV fuselage shell by a secondary tube clamp 3 and a main tube clamp 2. A motor mount 4 is installed at the distal end of the movable arm 102.

[0031] The folding component 7 includes a first sleeve 701 and a second sleeve 702 with a straight notch on the outer wall. The outer walls of the first sleeve 701 and the second sleeve 702 are provided with third fastening holes 703 on both sides of the corresponding straight notch. The straight notch is arranged along the axial direction of the first sleeve 701 and the second sleeve 702.

[0032] After the end of the fixed arm 101 is inserted into the first clamping sleeve 701, the third fastening hole 703 is tightened by the bolt assembly, thereby clamping and fixing the fixed arm 101 by the first clamping sleeve 701. Similarly, after the end of the movable arm 102 is inserted into the second clamping sleeve 702, the third fastening hole 703 is tightened by the bolt assembly, thereby clamping and fixing the movable arm 102 by the second clamping sleeve 702.

[0033] The first clamping sleeve 701 and the second clamping sleeve 702 are respectively fixed with a first fixing plate 704 and a second fixing plate 705 at their adjacent ends. The top of the first fixing plate 704 is provided with a connecting groove 706, and the top of the second fixing plate 705 is provided with a connecting platform 707. The connecting platform 707 is rotatably connected to the connecting groove 706 through a rotating shaft. The bottom of the first fixing plate 704 and the second fixing plate 705 are provided with connecting holes, and the bottoms of the two are fixed by bolts.

[0034] like Figure 2 , 13 As shown in Figure 14, in this embodiment, a tripod 9 is mounted on the bottom of the fuselage 8, and a searchlight 10 is mounted on the tripod 9. A camera 11 and a radar 12 are mounted on the side of the fuselage 8.

[0035] The fuselage 8 has multiple sunken battery compartments 13, and the cover plate 801 has battery insertion holes 802 corresponding to the positions of the battery compartments 13. The sunken design of the battery compartments 13 protects the batteries and shifts the overall center of gravity of the drone, making its flight more stable.

[0036] like Figures 15 to 17 As shown, the motor base 4 includes two symmetrically arranged base bodies 401 on a horizontal plane. Each base body 401 has a groove 402 on its mating surface for clamping and engaging with the arm body 1. Each base body 401 has a foot plate 403 on both sides, with mounting holes on the foot plate 403. After the two base bodies 401 are assembled, the foot plates 403 are fixed together with bolts. A connecting seat 404 is bolted to the side of the base body 401 facing away from the groove 402, and the motor 5 is mounted on the connecting seat 404.

[0037] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. An eight-rotor heavy-duty unmanned aerial vehicle (UAV) comprising a fuselage (8), a cover plate (801) being provided on the top of the fuselage (8), eight foldable rotor arms (1) being arranged around the fuselage (8), a motor mount (4) being mounted at the far end of each rotor arm (1), a motor (5) being mounted on the motor mount (4), and blades (6) being mounted on the drive shaft of each motor (5), characterized in that: The rotor arm (1) is equipped with a plurality of main tube clamps (2) at its proximal end. The top of the main tube clamps (2) is connected to the cover plate (801) and the top of the main tube clamps (2) is connected to the fuselage (8). The main clamp (2) includes a clamping part (201) and an end plate (202). The clamping part (201) includes a left half-hoop (201-1) and a right half-hoop (201-2). The lower ends of the left half-hoop (201-1) and the right half-hoop (201-2) are integrally formed. The left half-hoop (201-1) and the right half-hoop (201-2) are symmetrically arranged, and their arc surfaces form a circular clamping hole (201-3). There is a gap between the upper ends of the left half-hoop (201-1) and the right half-hoop (201-2), and both the left half-hoop (201-1) and the right half-hoop (201-2) are provided with an extension (201-4) at their upper ends. The body (201-4) is provided with a first fastening hole (201-5); there are two end plates (202), which are located on both sides of the clamping part (201). The end plate (202) is provided with a through hole (202-1) corresponding to the circular clamping hole (201-3). The diameter of the through hole (202-1) is the same as the diameter of the circular clamping hole (201-3). The end plate (202) is integrally formed with the left half hoop (201-1), and there is a gap between the end plate (202) and the right half hoop (201-2). The upper and lower ends of the end plate (202) are provided with a first mounting hole (202-2).

2. The eight-rotor heavy-load UAV according to claim 1, characterized in that: A secondary tube clamp (3) is installed at the near end of the rotor arm (1). The secondary tube clamp (3) is located between two adjacent main tube clamps (2). The secondary tube clamp (3) includes two clamp bodies (301) arranged symmetrically. The clamp (301) includes an arc-shaped segment (301-1) with its opening facing the side. Horizontal segments (301-2) are provided at both the upper and lower positions of the arc-shaped segment (301-1). The horizontal segments (301-2) are connected to the arc-shaped segment (301-1) through a vertical segment (301-3). A bent segment (301-4) is provided at one end of the horizontal segment (301-2) on the same side as the opening of the arc-shaped segment (301-1). The bent segment (301-4) extends toward the opening side of the arc-shaped segment (301-1), and a vertically arranged butt joint segment (301-5) is provided at the extended end of the bent segment (301-4). The horizontal section (301-2) is provided with a second mounting hole (301-6); the docking section (301-5) and the vertical section (301-3) are both provided with a second fastening hole (301-7), and the two second fastening holes (301-7) are arranged on the same axis.

3. The eight-rotor heavy-load UAV according to claim 1, characterized in that: The end plate (202) is provided with a plurality of hollow holes (202-3); the hollow holes (202-3) are elongated and extend in the vertical direction.

4. The eight-rotor heavy-load UAV according to claim 1, characterized in that: Both ends of the end plate (202) are provided with laterally extending support legs (202-4), and the first mounting hole (202-2) is provided on the support legs (202-4).

5. The eight-rotor heavy-load UAV according to claim 1, characterized in that: Threaded holes (202-5) are provided on both the left and right side walls of the end plate (202).

6. The eight-rotor heavy-load UAV according to claim 1, characterized in that: The rotor arm (1) includes a fixed arm (101) and a movable arm (102), which are connected by a folding member (7).

7. The eight-rotor heavy-load UAV according to claim 1, characterized in that: The folding component (7) includes a first sleeve (701) and a second sleeve (702) with a cross-shaped notch on the outer wall. The first sleeve (701) and the second sleeve (702) have third fastening holes (703) on both sides of the corresponding cross-shaped notch on the outer wall. The first clamp (701) and the second clamp (702) are respectively fixed with a first fixing plate (704) and a second fixing plate (705) at their adjacent ends. The top of the first fixing plate (704) is provided with a connecting groove (706), and the top of the second fixing plate (705) is provided with a connecting platform (707). The connecting platform (707) is rotatably connected to the connecting groove (706). The bottoms of the first fixing plate (704) and the second fixing plate (705) are fixed by bolts.

8. The eight-rotor heavy-load UAV according to claim 1, characterized in that: The bottom of the fuselage (8) is provided with a tripod (9), and a searchlight (10) is provided on the tripod (9).

9. The eight-rotor heavy-load UAV according to claim 1, characterized in that: The side of the fuselage (8) is equipped with a camera (11) and a radar (12).

10. The eight-rotor heavy-load UAV according to claim 1, characterized in that: The fuselage (8) has multiple sunken battery compartments (13) arranged on it, and the cover plate (801) has a battery insertion hole (802) corresponding to the position of the battery compartment (13).

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