Rotor structure for unmanned aerial vehicle

Abstract

The present invention discloses a rotor structure for an unmanned aerial vehicle (UAV), comprising a base and two symmetrically arranged blades, one end of each blade being rotatably inserted into the base, the top of the base being provided with a through opening corresponding to the blade, a rotating rod being rotatably inserted into the base, the top of each rotating rod being fixedly connected to two symmetrically arranged balancing rods, a torsion spring being sleeved on the rotating rod, the ends of each torsion spring being fixedly connected to the rotating rod and the base, respectively, and a first bevel gear being fixedly sleeved on the rotating rod. The present invention simplifies the directional control mechanism of an unmanned helicopter, eliminating the complex swash plate linkage mechanism. With the help of the balancing rod inertia mechanism, the directional control function is achieved by controlling the periodic fluctuation of the rotation speed through the principle of inertia. Compared with the traditional swash plate linkage directional control method, this method has the advantages of simple structure, low damage resistance, light weight, and high reliability.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle (UAV) rotors, and in particular to a rotor structure for a UAV. Background Art

[0002] Currently, drones are widely used in a variety of fields, including dynamic land use monitoring, mineral resource exploration, geological environment and disaster surveys, cadastral surveying, and map updates. However, drones are powered, unmanned aircraft that can fly autonomously or remotely and can be recovered for single or multiple uses. They have a wide range of applications in scientific research, civilian sectors, and the military.

[0003] The drone's directional control still utilizes a traditional swashplate automatic tilt mechanism. A swashplate automatic tilt mechanism is a specialized device used in helicopters to change the rotor pitch direction and blade pitch angle. It controls the helicopter's flight state. It is mounted on the rotor shaft via a spherical sleeve, which is connected to the collective pitch lever and can slide up and down the rotor shaft. A non-rotating ring, called the inner ring, sits on the sleeve's spherical surface and is connected to the cyclic pitch lever. The inner ring can tilt in any direction along the sleeve. The outer ring is the rotating component, rotating around the inner ring via rolling bearings and connected to the blades via pull rods for simultaneous movement. When the collective pitch lever is manipulated, the sleeve moves the entire automatic tilt mechanism upward or downward, simultaneously increasing or decreasing the pitch of each blade, causing the helicopter to ascend or descend. Pushing the cyclic pitch lever tilts the inner ring around the sleeve, which in turn tilts the outer ring, pulling the blades to periodically change pitch, tilting the rotor's rotational plane. This allows the helicopter to fly in the direction of the horizontal component of the rotor thrust, thus achieving flight control.

[0004] However, the existing swash plate automatic tilt mechanism has the disadvantages of being complex in structure and difficult to manufacture. In addition, it requires mechanical control of three additional degrees of freedom and has a heavy overall mass. Summary of the Invention

[0005] The purpose of the present invention is to solve the problem that the existing UAV rotor generally adopts a swash plate type automatic tilt device, which has a complex structure and high manufacturing difficulty, and to propose a rotor structure for a UAV.

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] A rotor structure for an unmanned aerial vehicle comprises a base and two symmetrically arranged blades, one end of the blade being rotatably inserted into the base, a through opening corresponding to the blade being provided at the top of the base, a rotating rod being rotatably inserted into the base, the top of the rotating rod being fixedly connected to two symmetrically arranged balance rods, a torsion spring being sleeved on the rotating rod, the two ends of the torsion spring being fixedly connected to the rotating rod and the base respectively, a first bevel gear being fixedly sleeved on the rotating rod, and an end of the blade close to the rotating rod being fixedly connected to a second bevel gear meshing with the first bevel gear.

[0008] Preferably, a fixing column corresponding to the rotating rod is fixedly connected in the base, a plurality of protrusions are provided on the bottom of the rotating rod, and a plurality of grooves corresponding to the protrusions are provided on the top of the fixing column.

[0009] Preferably, a slot corresponding to the torsion spring is provided in the fixing column.

[0010] Preferably, both ends of the balance bar are fixedly connected with balance blocks.

[0011] Beneficial effects:

[0012] The present invention simplifies the direction control mechanism of the unmanned helicopter and eliminates the complex swash plate linkage mechanism. With the help of the balance bar inertia mechanism, the direction control function is achieved by controlling the periodic fluctuation of the rotation speed through the inertia principle. Compared with the traditional swash plate linkage direction control method, this method has the advantages of simple structure, not easy to damage, light weight, and high reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is a schematic structural diagram of a rotor structure for a UAV proposed by the present invention;

[0014] Figure 2 This is a schematic diagram of the structure of a blade in a rotor structure for a UAV proposed by the present invention;

[0015] Figure 3 This is a schematic structural diagram of a balancing rod in a rotor structure for a UAV proposed by the present invention;

[0016] Figure 4 This is a schematic structural diagram of a base in a rotor structure for a UAV proposed by the present invention;

[0017] Figure 5 This is a schematic structural diagram of a torsion spring in a rotor structure for a UAV proposed by the present invention.

[0018] In the figure: 1 base, 2 blades, 3 rotating rod, 4 balance rod, 5 torsion spring, 6 first bevel gear, 7 second bevel gear, 8 fixing column, 9 balance block. DETAILED DESCRIPTION

[0019] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0020] Reference Figure 1-5 A rotor structure for a drone includes a base 1 and two symmetrically arranged blades 2. One end of the blade 2 is rotatably inserted into the base 1. The top of the base 1 is provided with a through hole corresponding to the blade 2. A rotating rod 3 is rotatably inserted into the base 1 for mounting a balancing rod 4.

[0021] In this embodiment, a fixing column 8 corresponding to the rotating rod 3 is fixedly connected to the base 1 for supporting the rotating rod 3. The bottom of the rotating rod 3 is provided with a plurality of protrusions, and the top of the fixing column 8 is provided with a plurality of grooves corresponding to the protrusions.

[0022] In this embodiment, two symmetrically arranged balance rods 4 are fixedly connected to the top of the rotating rod 3 to play an inertial balancing role. Balance weights 9 are fixedly connected to both ends of the balance rod 4. A torsion spring 5 is sleeved on the rotating rod 3, and a slot corresponding to the torsion spring 5 is provided in the fixing column 8.

[0023] In this embodiment, the two ends of the torsion spring 5 are fixedly connected to the rotating rod 3 and the base 1 respectively. A first bevel gear 6 is fixedly sleeved on the rotating rod 3. The end of the blade 2 close to the rotating rod 3 is fixedly connected to a second bevel gear 7 that meshes with the first bevel gear 6, which is used to drive the blade 2 to rotate.

[0024] In this embodiment, when flight direction needs to be changed, base 1 is controlled to accelerate periodically, accelerating before reaching a specific position within a revolution. However, due to inertia, the balance bar 4's rotational speed lags, causing it to rotate relative to base 1. Through the bevel gear mechanism, the rotation of the balance bar 4 relative to base 1 drives the rotation of the blades 2, thereby changing the angle of attack of the blades 2. After passing this specific position, base 1's rotational speed returns to its original speed, and the torsion spring 5 and inertial forces restore the rotor to its normal speed. When the rotor passes this specific position, one rotor is at a high angle of attack, while the other is at a low angle of attack, generating a steering torque. Due to the precession effect, directional control of the helicopter is achieved.

[0025] This embodiment simplifies the unmanned helicopter's directional control mechanism, eliminating the complex swashplate linkage mechanism. Instead, with the aid of a stabilizer bar inertia mechanism, directional control is achieved by controlling periodic rotational speed fluctuations through the inertial principle. Compared to traditional swashplate linkage directional control methods, this approach offers advantages such as a simpler structure, improved durability, lighter weight, and higher reliability.

[0026] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution and inventive concept of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. A rotor structure for an unmanned aerial vehicle, comprising a base (1) and two symmetrically arranged blades (2), characterized in that: One end of the blade (2) is rotatably inserted into the base (1); a through opening corresponding to the blade (2) is provided on the top of the base (1); a rotating rod (3) is rotatably inserted into the base (1); the top of the rotating rod (3) is fixedly connected to two symmetrically arranged balance rods (4); a torsion spring (5) is sleeved on the rotating rod (3); the two ends of the torsion spring (5) are respectively fixedly connected to the rotating rod (3) and the base (1); a first bevel gear (6) is fixedly sleeved on the rotating rod (3); and one end of the blade (2) close to the rotating rod (3) is fixedly connected to a second bevel gear (7) meshing with the first bevel gear (6).

2. The rotor structure for a drone according to claim 1, characterized in that: A fixing column (8) corresponding to the rotating rod (3) is fixedly connected inside the base (1); a plurality of protrusions are provided on the bottom of the rotating rod (3); and a plurality of grooves corresponding to the protrusions are provided on the top of the fixing column (8).

3. The rotor structure for a drone according to claim 2, characterized in that: A slot corresponding to the torsion spring (5) is provided in the fixing column (8).

4. The rotor structure for a drone according to claim 1, characterized in that: Both ends of the balancing rod (4) are fixedly connected with balancing blocks (9).

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