Helicopter rotor wing

Abstract

The utility model relates to a helicopter rotor, which comprises a main shaft and two propeller discs installed on the main shaft, three propeller clamps are respectively detachably fixed on the two propeller discs, the three propeller clamps are uniformly distributed around the circumferential sides of the propeller discs, each propeller clamp is detachably fixed with a propeller blade, and the propeller blades are fixed on the propeller clamps. One end of the paddle clamp is movably connected to the supporting arm, close to the center, of the paddle disc through a control universal joint, and the other end of the paddle clamp is movably connected to the tail end of the supporting arm of the paddle disc. By arranging the control universal joint playing a role in movable connection between the propeller disc and the propeller clamp, stress in different directions can be effectively converted into micro sliding friction, so that damage to the structure caused by the strong stress is greatly reduced, a propeller can move more smoothly in the flying process of an airplane, the resonance risk is reduced, and the service life of the airplane is prolonged. And the structural safety is greatly improved.

Description

Technical Field

[0001] The utility model relates to the technical field of helicopter rotors, in particular to a helicopter rotor. Background Art

[0002] The rotor is a crucial component of a helicopter. During flight, it generates both lift and thrust. Furthermore, it also functions similarly to the ailerons and elevators of an airplane.

[0003] In the prior art, for example, patent document CN100436257C discloses a jointless rotor, in particular a rotor for a rotorcraft, comprising a rotor hub (2), a rotor rod (4) having a rotor axis (A), a torque transmission element (6) connected to the rotor rod in a torsionally fixed manner, at least one rotor blade (8), and a blade joint on the rotor hub side having a blade joint ring (10) for eliminating centrifugal force, wherein the blade joint ring surrounds the rotor axis (A) or the rotor rod and is connected to the torque transmission element (6) in a torsionally fixed manner (12, 14).

[0004] The above-mentioned existing technical solutions have the following defects: the above-mentioned rotor is not provided with joints. During actual operation, the strong stress in different directions of the rotor will cause damage to the structure, making the movement of the propeller less smooth during the flight of the aircraft, increasing the risk of resonance and reducing the safety of the structure. Utility Model Content

[0005] In response to the shortcomings of the existing technology, the purpose of the present invention is to provide a helicopter rotor that can effectively convert stresses in different directions into a small amount of sliding friction, thereby greatly reducing the damage caused to the structure by these strong stresses, making the movement of the propeller smoother during flight, reducing the risk of resonance, and greatly improving structural safety.

[0006] The above-mentioned utility model object of the present invention is achieved through the following technical solutions:

[0007] A helicopter rotor comprises a main shaft and two propeller discs mounted on the main shaft, wherein three propeller clamps are detachably fixed to each of the two propeller discs, and the three propeller clamps are evenly distributed around the circumference of the propeller disc. A propeller blade is detachably fixed to each of the propeller clamps, and one end of the propeller clamp is movably connected to a support arm near the center of the propeller disc by controlling a universal joint, and the other end of the propeller clamp is movably connected to the end of the support arm of the propeller disc.

[0008] As a further technical solution of the present invention: the control universal joint includes a ball joint, a bearing outer ring, a bearing inner ring and a roller, the roller is installed between the bearing outer ring and the bearing inner ring, the bearing inner ring is provided with an inner spherical surface that slides with the outer spherical surface of the ball joint, the bearing outer ring is installed in the propeller clamp, and one end of the ball joint is connected to the propeller disc.

[0009] As a further technical solution of the present invention: a plurality of rollers are provided, and the plurality of rollers are evenly spaced and distributed between the bearing outer ring and the bearing inner ring.

[0010] As a further technical solution of the present invention: the roller is arranged in a conical shape, and the diameter of one end of the roller gradually decreases toward the other end.

[0011] As a further technical solution of the present invention: an annular groove is provided on the circumferential outer wall of the bearing inner ring, the roller is installed in the annular groove and rollingly engages with the bottom wall of the annular groove, and the inner wall of the bearing outer ring is provided with a conical arc surface that rolls with the roller.

[0012] As a further technical solution of the present invention: an oil filling hole is opened at the center of the bearing inner ring and passes through the bearing inner ring to the inner spherical surface.

[0013] As a further technical solution of the present invention: an end of the ball joint away from the outer spherical surface is integrally formed and fixedly connected with a mounting shaft, and the mounting shaft is connected to the propeller disc.

[0014] As a further technical solution of the present invention: a damping frame is fixed to one end of the propeller clamp close to the propeller blade, a damper bearing is installed in the damping frame, damping rubber is provided between the damping frame and the damper bearing, a propeller shaft is installed in the damper bearing, and the end of the propeller shaft away from the damper bearing is connected to the end of the support arm of the propeller disc.

[0015] In summary, the present invention has at least one of the following beneficial technical effects:

[0016] 1. The present invention discloses a helicopter rotor blade that utilizes a control universal joint that acts as a movable connection between the rotor disc and the blade clamp. The helicopter's flight attitude is controlled by controlling the pitch angle of the propeller, which is fixed to the blade clamp. This angle change is achieved by controlling the rotation of the blade clamp. When the angle between the blade clamp and the rotor disc changes, the bearing portion of the control joint converts sliding friction into rolling friction, significantly improving rotational flexibility and reducing friction, making the control system more flexible.

[0017] 2. Rotor rotation and fuselage vibrations exert varying forces on the connection between the propeller clamp and the disc. The ball-joint design of the control joint effectively converts these forces into minimal sliding friction, significantly reducing the structural damage caused by these intense forces. This allows for smoother propeller movement during flight and reduces the risk of resonance. Propeller rotation generates significant centrifugal force, and the ball-joint design effectively increases the force-bearing area, making the wing structure more stable and reliable, significantly enhancing structural safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the overall structure of the utility model.

[0019] Figure 2 This is a schematic diagram showing the overall structure of the paddle disc of the present invention.

[0020] Figure 3 This is a cross-sectional view showing the paddle disc of the present invention.

[0021] Figure 4 This is a schematic diagram showing the overall structure of the control universal joint of the utility model.

[0022] Figure 5 This is a forward explosion diagram showing the control of the universal joint of the utility model.

[0023] Figure 6 This is a schematic diagram showing the reverse explosion of controlling the universal joint of the utility model.

[0024] Figure 7 It is the main view of the present utility model.

[0025] Figure 8 for Figure 7 Cross-sectional view along BB.

[0026] Figure numerals: 10, main shaft, 101, propeller disc; 102, propeller clamp; 103, propeller blade; 1, ball joint; 11, outer spherical surface; 2, bearing outer ring; 21, tapered arc surface; 3, bearing inner ring; 31, inner spherical surface; 32, ring groove; 33, oil filling hole; 4, roller; 5, mounting shaft; 6, damping frame; 7, damper bearing; 8, damping rubber; 9, propeller shaft. DETAILED DESCRIPTION

[0027] The technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application; it is obvious that the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application.

[0028] In the description of this application, it should be noted that the terms "upper," "lower," "inner," "outer," "top / bottom," and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate the description of this application and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0029] In the description of this application, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "provided with," "mounted / connected," and "connected" should be understood in a broad sense. For example, "connected" can mean a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on the specific circumstances. Example

[0030] Reference Figure 1-3 , is a helicopter rotor disclosed in the utility model, comprising a main shaft 10 and two propeller discs 101 mounted on the main shaft 10, three propeller clamps 102 are detachably fixed on the two propeller discs 101, and the three propeller clamps 102 are evenly distributed around the circumference of the propeller disc 101, and a blade 103 is detachably fixed on each propeller clamp 102, one end of the propeller clamp 102 is movably connected to a support arm near the center of the propeller disc 101 by controlling a universal joint, and the other end of the propeller clamp 102 is movably connected to the end of the support arm of the propeller disc 101.

[0031] Reference Figure 4-8 The control universal joint includes a ball joint 1, a bearing outer ring 2, a bearing inner ring 3, and a roller 4. Roller 4 is mounted between the bearing outer ring 2 and the bearing inner ring 3. The bearing inner ring 3 has an inner spherical surface 31 that slidably fits the outer spherical surface 11 of the ball joint 1. The bearing outer ring 2 is mounted within the propeller clamp 102, and one end of the ball joint 1 is connected to the propeller disc 101.

[0032] In this embodiment, a plurality of rollers 4 are provided, and the plurality of rollers 4 are evenly spaced and distributed between the bearing outer ring 2 and the bearing inner ring 3. The rollers 4 are tapered, and the diameter of the rollers 4 gradually decreases from one end toward the other end.

[0033] An annular groove 32 is defined on the outer peripheral wall of the bearing inner ring 3. Rollers 4 are mounted within this groove and engage in rolling engagement with its bottom wall. The inner wall of the bearing outer ring 2 features a tapered arc surface 21 that engages with the rollers 4 in rolling engagement. An oil injection hole 33 is located at the center of the bearing inner ring 3, extending from the inner ring 3 to the inner spherical surface 31. During maintenance, lubricating oil is injected through this hole 33 between the inner spherical surface 31 and the outer spherical surface 11, thereby reducing friction between the ball joint 1 and the bearing inner ring 3 and extending the service life of the helicopter rotor control universal joint.

[0034] The end of the ball joint 1 away from the outer spherical surface 11 is integrally formed and fixedly connected with a mounting shaft 5, which is connected to the paddle disc 101. Figure 2-3 The control universal joint is used on the helicopter rotor to connect the propeller disc and the propeller clamp on the helicopter rotor. The mounting shaft 5 of the ball joint 1 is installed on the propeller disc, and the bearing outer ring 2 is installed on the propeller clamp. The helicopter propeller is detachably fixed on the propeller clamp. The propeller disc and the propeller clamp are assembled together through the control universal joint to play the role of active connection.

[0035] A damping frame 6 is fixed to the end of the propeller clamp 102 close to the propeller blade, and a damper bearing 7 is installed in the damping frame 6. A damping rubber 8 is provided between the damping frame 6 and the damper bearing 7. A propeller shaft 9 is installed in the damper bearing 7. The end of the propeller shaft 9 away from the damper bearing 7 is connected to the end of the support arm of the propeller disc 101.

[0036] The present invention is based on the following principles: It discloses a helicopter rotor with a control universal joint that acts as a flexible connection between the propeller disc and the blade clamp. The helicopter's flight attitude is controlled by controlling the pitch angle of the propeller, which is fixed to the blade clamp. This angle change is achieved by controlling the rotation of the blade clamp. When the angle between the blade clamp and the propeller disc changes, the bearing portion of the control joint converts sliding friction into rolling friction, significantly improving rotational flexibility and reducing friction, making the control system more flexible.

[0037] The embodiments of this specific implementation method are all preferred embodiments of the present utility model, and are not intended to limit the scope of protection of the present utility model. Therefore, any equivalent changes made based on the structure, shape, and principle of the present utility model should be included in the scope of protection of the present utility model.

Claims

1. A helicopter rotor, comprising a main shaft (10) and two propeller discs (101) mounted on the main shaft (10), wherein three propeller clamps (102) are detachably fixed to each of the two propeller discs (101), the three propeller clamps (102) being evenly distributed around the circumference of the propeller disc (101), and a propeller blade (103) being detachably fixed to each of the propeller clamps (102), characterized in that: One end of the propeller clamp (102) is movably connected to a support arm near the center of the propeller disc (101) by controlling a universal joint, and the other end of the propeller clamp (102) is movably connected to the end of the support arm of the propeller disc (101).

2. A helicopter rotor according to claim 1, characterized in that: The control universal joint includes a ball joint (1), a bearing outer ring (2), a bearing inner ring (3) and a roller (4), wherein the roller (4) is installed between the bearing outer ring (2) and the bearing inner ring (3), and the bearing inner ring (3) is provided with an inner spherical surface (31) that slides with the outer spherical surface (11) of the ball joint (1), the bearing outer ring (2) is installed in the propeller clamp (102), and one end of the ball joint (1) is connected to the propeller disc (101).

3. A helicopter rotor according to claim 2, characterized in that: There are multiple rollers (4), and the multiple rollers (4) are evenly spaced and distributed between the bearing outer ring (2) and the bearing inner ring (3).

4. A helicopter rotor according to claim 2, characterized in that: The roller (4) is arranged in a conical shape, and the diameter of one end of the roller (4) gradually decreases towards the other end.

5. The helicopter rotor according to claim 2, characterized in that: The outer wall of the bearing inner ring (3) is provided with an annular groove (32), the roller (4) is installed in the annular groove (32) and is in rolling engagement with the bottom wall of the annular groove (32), and the inner wall of the bearing outer ring (2) is provided with a conical arc surface (21) in rolling engagement with the roller (4).

6. A helicopter rotor according to claim 2, characterized in that: An oil injection hole (33) is provided at the center of the bearing inner ring (3) and passes through the bearing inner ring (3) to the inner spherical surface (31).

7. The helicopter rotor according to claim 2, characterized in that: An end of the ball joint (1) away from the outer spherical surface (11) is integrally formed and fixedly connected with a mounting shaft (5), and the mounting shaft (5) is connected to the paddle disc (101).

8. The helicopter rotor according to claim 1, characterized in that: A damping frame (6) is fixed to one end of the propeller clamp (102) close to the propeller blade (103), a damper bearing (7) is installed in the damping frame (6), a damping rubber (8) is provided between the damping frame (6) and the damper bearing (7), a propeller shaft (9) is installed in the damper bearing (7), and the end of the propeller shaft (9) away from the damper bearing (7) is connected to the end of the support arm of the propeller disc (101).

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