Coaxial octo-copter unmanned aerial vehicle

Abstract

The utility model relates to unmanned plane technical field especially, it relates to coaxial eight rotor unmanned plane. The utility model provides such coaxial eight rotor unmanned plane, including fuselage, battery, sliding frame, support block, support rod, connecting block, rotor group, foot stool and drive assembly, the fuselage bottom is detachably connected with battery through quick -detach structure, and the outside of fuselage is fixed with a support block in four directions of front, back, left and right, and all have support rod rotatably connected on the support block, and the outside end of support rod is connected with rotor group, and rotor group adopts coaxial double propeller configuration, and all have connecting block connected on the inside end of support rod top. Realize rotor group automatic folding / unfolding through drive assembly, and more than 40% transverse dimension can be reduced under non -working condition, and the portability is improved and the risk of knock damage in the storage and transportation process is reduced.

Description

Technical Field

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

[0002] In the field of civilian and industrial drones, multi-rotor drones are widely used in surveying, inspection, and logistics due to their flexible control and stable hovering. However, existing multi-rotor drones have significant limitations in portability and structural design: the rotor arms of traditional fixed-wing multi-rotor drones are mostly rigid fixed structures, resulting in a large lateral dimension of the entire aircraft, making them inconvenient to carry in scenarios such as field operations and indoor transportation. Moreover, the rotors are prone to deformation due to impacts during storage and transportation, affecting flight accuracy. Although some foldable models can achieve rotor folding, they mostly use a manual folding structure, requiring manual operation of each rotor arm to rotate into place. The folding / unfolding process takes 3-5 minutes, which is cumbersome and the stability of the folded state is not reliable enough. It is easy for it to automatically unfold due to vibration during transportation, posing a safety hazard.

[0003] Therefore, developing a multi-rotor drone that can achieve automated folding / unfolding while maintaining portability has become a pressing technical problem to be solved in this field. Utility Model Content

[0004] In order to overcome the shortcomings mentioned in the background art, the present invention provides a coaxial octocopter drone.

[0005] The technical implementation scheme of this utility model is as follows: a coaxial octocopter drone, including a fuselage, a battery, sliding frames, support blocks, support rods, connecting blocks, rotor assemblies, landing gear, and a drive assembly. The battery is detachably connected to the bottom of the fuselage via a quick-release structure. A support block is fixed at each of the four positions on the outside of the fuselage: front, rear, left, and right. A support rod is rotatably connected to each support block. A rotor assembly is connected to the outer end of the support rod. The rotor assembly adopts a coaxial dual-propeller configuration. A connecting block is connected to the inner end of the top of each support rod. Slide rails are provided on the top of the fuselage corresponding to the left, right, front, and rear sides. Four sliding frames are slidably connected to the fuselage via slide rails. The outer end of the sliding frames is movably connected to the connecting block on the corresponding side. Landing gears are symmetrically fixed at the bottom of the fuselage. A drive assembly is provided on the top of the fuselage.

[0006] Furthermore, the rotor blades of the rotor assembly are made of modified polyoxymethylene material.

[0007] Furthermore, the inner wall of the slide rail that mates with the sliding frame in the drone is inlaid with a wear-resistant polytetrafluoroethylene layer.

[0008] Furthermore, the drive assembly includes a motor, a screw, a lifting plate, and movable blocks. The motor is embedded and fixed in the center of the top of the machine body. The screw is coaxially connected to the output shaft of the motor. The lifting plate is threaded onto the screw. A cap is integrally formed at the top of the screw to limit the extreme displacement height of the lifting plate. Movable blocks are rotatably connected to the four ends of the outer side of the lifting plate (front, rear, left, and right). The free end of the movable block is rotatably connected to the inner end of the corresponding side sliding frame.

[0009] Furthermore, it also includes a movable frame and a buffer spring. The movable frame is slidably connected to the bottom of the tripod via two guide rods. The sliding mating surfaces of the guide rods and the tripod are provided with a damping layer. A buffer spring is sleeved on the outside of the guide rods. The upper and lower ends of the buffer spring are connected to the bottom of the tripod and the top of the movable frame, respectively.

[0010] Furthermore, a silicone cushioning pad is glued to the bottom of the mobile frame.

[0011] The present invention has the following advantages: 1. The rotor assembly can be automatically folded / unfolded through the drive component. In the non-working state, the lateral size can be reduced by more than 40%, which improves portability and reduces the risk of bumps and damage during storage and transportation.

[0012] 2. The UAV adopts a coaxial dual-propeller counter-rotating design, which can counteract the counter-torque of a single rotor in real time, eliminating the need for a tail rotor balancing mechanism, reducing the risk of flight deviation caused by torque imbalance, and enhancing the ability to resist airflow interference.

[0013] 3. The landing gear is equipped with a buffer spring and a damping layer to form a two-stage buffer structure, which effectively absorbs landing impact energy, protects the fuselage structure and internal components, and improves landing stability. Attached Figure Description

[0014] Figure 1 This is a three-dimensional structural diagram of the present invention.

[0015] Figure 2 This is a cross-sectional view of the lifting plate component of this utility model.

[0016] Figure 3 This is a three-dimensional structural diagram of the movable block, sliding frame, and support block of this utility model.

[0017] Figure 4 This is a three-dimensional structural diagram of the components of this utility model, including the legs, movable frame, and buffer springs.

[0018] Figure 5 This is a schematic diagram of the folded state of this utility model.

[0019] In the above attached diagram: 1: fuselage, 2: battery, 3: motor, 4: screw, 5: lifting plate, 6: movable block, 7: sliding frame, 8: support block, 9: support rod, 10: connecting block, 11: rotor assembly, 12: landing gear, 13: movable frame, 14: buffer spring. Detailed Implementation

[0020] Example: Coaxial octocopter UAV, such as Figure 1 - Figure 5 As shown, the aircraft includes a fuselage 1, a battery 2, a sliding frame 7, support blocks 8, support rods 9, connecting blocks 10, rotor assemblies 11, landing gear 12, and a drive assembly. The battery 2 is detachably connected to the bottom of the fuselage 1 via a quick-release mechanism. Support blocks 8 are fixed at the front, rear, left, and right sides of the outer side of the fuselage 1. Support rods 9 are rotatably connected to each support block 8 via pins. Rotor assemblies 11 are rigidly connected to the outer ends of support rods 9 via flanges. The rotor assemblies 11 adopt a coaxial twin-propeller configuration, with each rotor assembly 11 containing two counter-rotating rotors, forming an independent power shaft. The entire aircraft is equipped with eight rotors, which are made of modified polyoxymethylene material. The material has high strength and high rigidity mechanical properties, which can meet the anti-centrifugal force requirements when the rotor rotates at high speed and avoid deformation affecting aerodynamic performance. The inner end of the top of the support rod 9 is connected to the connecting block 10. The top of the fuselage 1 is equipped with slide rails corresponding to the left, right and front and rear sides. The four sliding frames 7 are slidably connected to the fuselage 1 through the slide rails. The inner wall of the slide rail is inlaid with a polytetrafluoroethylene wear-resistant layer, which can significantly reduce the sliding resistance between the sliding frame 7 and the slide rail, making the folding / unfolding action smoother. The outer end of the sliding frame 7 is movably connected to the connecting block 10 on the corresponding side. The bottom of the fuselage 1 is symmetrically fixed with a foot bracket 12, and the top of the fuselage 1 is equipped with a drive assembly.

[0021] like Figure 2 - Figure 3 and Figure 5 As shown, the drive assembly includes a motor 3, a screw 4, a lifting plate 5, and a movable block 6. The motor 3 is embedded and fixed at the center of the top of the machine body 1. The screw 4 is coaxially keyed to the output shaft of the motor 3. The lifting plate 5 is threaded onto the screw 4. The top of the screw 4 is integrally formed with a cap to limit the extreme displacement height of the lifting plate 5 and ensure that the lifting plate 5 will not detach from the screw 4. The four ends of the lifting plate 5, namely the front, rear, left, and right, are rotatably connected to the movable block 6. The free end of the movable block 6 is rotatably connected to the inner end of the corresponding side sliding frame 7 through a pin.

[0022] The drone adopts a coaxial octagonal layout. Through the counter-rotating motion of the upper and lower rotors in the rotor assembly 11, the anti-torque generated by a single rotor can be counteracted in real time, significantly improving the drone's attitude stability. It eliminates the need for a tail rotor balancing mechanism required in traditional single-rotor layouts, simplifying the power system structure, reducing the risk of flight deviation due to torque imbalance, and enhancing the overall aircraft's resistance to airflow interference. For portability, the four-sided rotor assembly 11 can achieve automated folding / unfolding: When the drone is not in operation, motor 3 is activated. The output shaft of motor 3 drives screw 4 to rotate. Screw 4 converts the rotational motion into axial linear motion of the lifting plate 5 through a helical pair, causing the lifting plate 5 to move downwards vertically. The lifting plate 5 pushes the sliding frame 7 along the slide rail of the fuselage 1 outwards via the movable block 6. The sliding frame 7 drives the support rod 9 to rotate downwards around the pin axis to a folded posture via the connecting block 10. At this time, the rotor assembly 11 is in a folded state. Figure 5 As shown, this design can reduce the overall lateral dimension of the aircraft by more than 40%, effectively reducing the risk of collision damage during storage and transportation. When a flight mission is required, the control motor 3 reverses its rotation, the screw 4 drives the lifting plate 5 to return to its original position, and the movable block 6 pulls the sliding frame 7 to slide inward along the slide rail. Then, the connecting block 10 drives the support rod 9 and the rotor assembly 11 to rotate upward, returning to a horizontal working posture and completing the automatic deployment action.

[0023] like Figure 1 and Figure 4 As shown, it also includes a movable frame 13 and a buffer spring 14. The movable frame 13 is slidably connected to the bottom of the tripod 12 via two guide rods. The sliding mating surfaces of the guide rods and the tripod 12 are provided with a damping layer. A buffer spring 14 is sleeved on the outside of the guide rods. The upper and lower ends of the buffer spring 14 are connected to the bottom of the tripod 12 and the top of the movable frame 13, respectively. A silicone buffer pad is glued to the bottom of the movable frame 13 to improve wear resistance and provide cushioning during landing. When the drone lands, the movable frame 13 contacts the ground first. The buffer spring 14 absorbs the impact energy through elastic deformation. Combined with the damping effect of the damping layer, it achieves two-stage cushioning, effectively reducing the impact of landing impact on the structure and internal components of the fuselage 1 and improving landing stability.

Claims

1. A coaxial octocopter unmanned aerial vehicle (UAV), characterized by: The fuselage (1) includes a battery (2), a sliding frame (7), a support block (8), a support rod (9), a connecting block (10), a rotor assembly (11), a landing gear (12), and a drive assembly. The battery (2) is detachably connected to the bottom of the fuselage (1) via a quick-release structure. A support block (8) is fixed at each of the four positions on the outside of the fuselage (1), in front, back, left, and right. A support rod (9) is rotatably connected to each support block (8). The rotor assembly (11) is connected to the outer end of the support rod (9). The rotor assembly (11) adopts a coaxial dual-propeller configuration. The connecting block (10) is connected to the inner end of the top of the support rod (9). The top of the fuselage (1) is provided with slide rails corresponding to the left, right, front, and rear sides. The four sliding frames (7) are slidably connected to the fuselage (1) via the slide rails. The outer end of the sliding frame (7) is movably connected to the connecting block (10) on the corresponding side. The landing gear (12) is symmetrically fixed at the bottom of the fuselage (1). The drive assembly is provided at the top of the fuselage (1).

2. The coaxial octocopter UAV according to claim 1, characterized in that: The rotor of the rotor assembly (11) is made of modified polyoxymethylene material.

3. The coaxial octocopter UAV according to claim 1, characterized in that: The inner wall of the slide rail that cooperates with the sliding frame (7) in the UAV is inlaid with a polytetrafluoroethylene wear-resistant layer.

4. The coaxial octocopter UAV according to claim 1, characterized in that: The drive assembly includes a motor (3), a screw (4), a lifting plate (5), and a movable block (6). The motor (3) is embedded and fixed in the center of the top of the machine body (1). The screw (4) is coaxially connected to the output shaft of the motor (3). The lifting plate (5) is threaded onto the screw (4). The top of the screw (4) is integrally formed with a top cap to limit the extreme displacement height of the lifting plate (5). The four ends of the lifting plate (5) on the outside, namely the front, rear, left, and right, are respectively rotatably connected to the movable block (6). The free end of the movable block (6) is rotatably connected to the inner end of the corresponding side sliding frame (7).

5. The coaxial octocopter UAV according to claim 1, characterized in that: It also includes a movable frame (13) and a buffer spring (14). The bottom of the leg (12) is slidably connected to the movable frame (13) through two guide rods. The sliding mating surface between the guide rods and the leg (12) is provided with a damping layer. The outer side of the guide rods is fitted with a buffer spring (14). The upper and lower ends of the buffer spring (14) are connected to the bottom of the leg (12) and the top of the movable frame (13) respectively.

6. The coaxial octocopter UAV according to claim 5, characterized in that: The bottom of the mobile frame (13) is glued with a silicone cushioning pad.

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