Propeller blade angle adjusting mechanism

Abstract

The utility model discloses a propeller blade angle adjusting mechanism which comprises a hollow positioning seat, a speed reducer is arranged in the hollow positioning seat, output shafts are arranged at the two ends of the speed reducer, the ends, away from the speed reducer, of the output shafts extend to the outer portion of the hollow positioning seat and are provided with U-shaped frames, and connecting columns are installed on the inner wall of one side of each U-shaped frame. A first shell is arranged at the end, away from the U-shaped frame, of the connecting column, a second shell is installed at the end, away from the U-shaped frame, of the first shell, triangular frames are arranged in the first shell and the second shell, limiting bases are arranged in the positions, on the outer sides of the triangular frames, of the first shell and the second shell at equal intervals, and a plurality of micro motors are installed on the inner walls of the triangular frames. According to the utility model, the inclination angles of the paddle bodies can be electrically adjusted, and the angles of the three paddle bodies can be integrally adjusted, so that the adjusting effect of the adjusting mechanism during use is improved, and the convenience of the adjusting mechanism during installation and maintenance is improved.

Description

Technical Field

[0001] This utility model relates to the technical field of propulsion systems for low-altitude aircraft, specifically to a propeller blade angle adjustment mechanism. Background Technology

[0002] A propeller consists of helical blades and a hub. The blades are the main part that generates thrust, and their shape design helps to effectively move the fluid during rotation, thereby generating thrust. It is a device that generates thrust to propel an aircraft. There are many types of aircraft, and low-altitude aircraft are one of them. Current fixed-blade propellers have many limitations, such as the inability to adjust the pitch according to the load characteristics of low-altitude aircraft, resulting in high energy consumption and inflexible handling of low-altitude aircraft. In order to improve these problems, it is particularly important to develop a propeller blade angle adjustment mechanism.

[0003] A high-efficiency adjustable pitch propeller, as described in reference announcement number CN211196594U, comprises a hub, a transmission hole, blades, and an adjustment mechanism. The adjustment mechanism uses a rotating rod to drive a rotating cylinder, which in turn rotates the blades to adjust the pitch. Furthermore, the second screw can be separated from the fixed post and the locking block, thus separating the blades from the hub and achieving pitch adjustment. The propeller can be matched with various engines, and the blades can be quickly installed and removed. This solves the problem that when a propeller has a fixed pitch, blade replacement can lead to incompatibility with some engines, and the blade replacement process is time-consuming. However, while this adjustment mechanism can be effectively applied, it typically only slightly adjusts the blade angle and requires manual operation. Therefore, its adjustment effect on low-altitude aircraft propeller blades often falls short of expectations, frequently causing inconvenience for users. Utility Model Content

[0004] The purpose of this utility model is to provide a propeller blade angle adjustment mechanism to solve the problem that although the adjustment mechanism mentioned in the background art can be well applied, it can usually only slightly adjust the blade angle and requires manual operation, so the adjustment effect of the adjustment mechanism on the propeller blade is still difficult to achieve the expected result.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a propeller blade angle adjustment mechanism, comprising a hollow positioning seat, a reducer being provided inside the hollow positioning seat, output shafts being provided at both ends of the reducer, the end of the output shaft away from the reducer extending to the outside of the hollow positioning seat and having a U-shaped frame, a connecting column being installed on the inner wall of one side of the U-shaped frame, a first housing being provided at the end of the connecting column away from the U-shaped frame, a second housing being installed at the end of the first housing away from the U-shaped frame, a tripod being provided inside the first housing and the second housing, and equally spaced limiting seats being provided inside the first housing and the second housing outside the tripod, a plurality of micro motors being installed on the inner wall of the tripod, a rotating shaft being installed at the output end of the micro motors via a coupling, the end of the rotating shaft away from the micro motor extending to the inside of the limiting seat and having a blade body, the end of the blade body away from the micro motor extending to the outside of the limiting seat, and the blade body being movably connected to the limiting seat.

[0006] Preferably, positioning bolts are installed at the corners of the outer wall of the hollow positioning seat, with one end of the positioning bolt extending through to the outside of the hollow positioning seat. The positioning bolts are used to secure the hollow positioning seat to the low-altitude aircraft.

[0007] Preferably, a rotary drive component is installed on the outer wall of the hollow positioning seat. One end of the rotary drive component extends into the interior of the hollow positioning seat and is connected to the input shaft of the reducer's outer wall. The rotary drive component is used to drive the reducer to operate.

[0008] Preferably, a circular plate is provided on the outer wall of the first housing outside the connecting column, and a column cylinder is provided on the outer wall of the circular plate outside the connecting column. The column cylinder is movably connected to the connecting column, and the column cylinder is provided to limit the positioning of one end of the connecting column.

[0009] Preferably, a plurality of bolts are installed on the outer wall of the first housing, one end of each bolt penetrating the first housing and connecting to the outer wall of the second housing, thereby enabling the first housing and the second housing to be installed and connected.

[0010] Preferably, a plurality of locking bolts are installed on the outer wall of the circular plate. One end of each locking bolt passes through the circular plate and is threadedly connected to the outer wall of the first housing. The locking bolts are used to install the circular plate onto the outer wall of the first housing.

[0011] Compared with the prior art, the beneficial effects of this utility model are: the propeller blade angle adjustment mechanism can not only electrically adjust the tilt angle of the blade body, but also adjust the angle of the three blade bodies as a whole, so as to improve the adjustment effect when using the adjustment mechanism, and improve the convenience of installation and maintenance of the adjustment mechanism.

[0012] (1) By starting the micro motor, the blade body can be driven to rotate via the rotating shaft. Due to the setting of the limit seat, the movement range of one end of the blade body is limited, thereby the tilt angle of the blade body can be electrically adjusted, thus improving the adjustment effect when the adjustment mechanism is used.

[0013] (2) The reducer is driven by the rotary drive component to operate, so that the reducer drives the U-shaped frame to rotate slightly outside the hollow positioning seat via the output shaft. This allows the U-shaped frame to drive the first housing to rotate accordingly via the connecting column, thereby adjusting the angle of the three blade bodies as a whole, which further improves the angle adjustment effect of the adjustment mechanism on the blade bodies.

[0014] (3) By tightening the locking bolts and bolts, the circular plate can be removed from the outer wall of the first housing, and the second housing can be removed from one end of the first housing, which makes it easier to clean and maintain the inner parts of the first and second housings. Then, by placing the hollow positioning seat on the low-altitude aircraft and calibrating the positioning bolt to the threaded hole reserved in the low-altitude aircraft, and then tightening the positioning bolt so that one end of the positioning bolt passes through the hollow positioning seat and is screwed into the threaded hole of the low-altitude aircraft, the hollow positioning seat can be bolted and installed, thereby improving the convenience of installation and maintenance of the adjustment mechanism. Attached Figure Description

[0015] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0016] Figure 2 This is a cross-sectional structural diagram of the present invention;

[0017] Figure 3 This utility model Figure 1 Enlarged structural diagram at point A in the middle;

[0018] Figure 4 This utility model Figure 1 Enlarged structural diagram at point B;

[0019] Figure 5 This utility model Figure 2 Enlarged structural diagram at point C.

[0020] In the diagram: 1. Hollow positioning seat; 2. Connecting column; 3. Blade body; 4. Positioning bolt; 5. Rotary drive component; 6. Reducer; 7. Output shaft; 8. U-shaped frame; 9. First housing; 10. Second housing; 11. Limiting seat; 12. Bolt component; 13. Locking bolt; 14. Circular plate; 15. Column; 16. Triangular frame; 17. Micro motor; 18. Rotating shaft. Detailed Implementation

[0021] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the scope of protection of the present utility model.

[0022] Please see Figure 1-5 An embodiment of this utility model is provided: a propeller blade angle adjustment mechanism, including a hollow positioning seat 1, with positioning bolts 4 installed at the corner positions of the outer wall of the hollow positioning seat 1, one end of the positioning bolts 4 penetrating to the outside of the hollow positioning seat 1.

[0023] In use, the positioning bolt 4 is used to secure the hollow positioning seat 1 to the low-altitude aircraft.

[0024] A rotary drive component 5 is installed on the outer wall of the hollow positioning seat 1. One end of the rotary drive component 5 extends into the interior of the hollow positioning seat 1 and is connected to the input shaft on the outer wall of the reducer 6.

[0025] In use, the reducer 6 is driven to operate by rotating the drive component 5.

[0026] The hollow positioning seat 1 is equipped with a reducer 6 inside. Both ends of the reducer 6 are equipped with output shafts 7. The end of the output shaft 7 away from the reducer 6 extends to the outside of the hollow positioning seat 1 and is equipped with a U-shaped frame 8. A connecting column 2 is installed on the inner wall of one side of the U-shaped frame 8. A circular plate 14 is provided on the outer wall of the first housing 9 outside the connecting column 2. A column cylinder 15 is provided on the outer wall of the circular plate 14 outside the connecting column 2. The column cylinder 15 is movably connected to the connecting column 2.

[0027] In use, the column tube 15 is set to limit the positioning of one end of the connecting column 2;

[0028] Several locking bolts 13 are installed on the outer wall of the circular plate 14. One end of the locking bolt 13 passes through the circular plate 14 and is threadedly connected to the outer wall of the first housing 9.

[0029] In use, the circular plate 14 is installed on the outer wall of the first housing 9 by means of the locking bolt 13;

[0030] The end of the connecting column 2 away from the U-shaped frame 8 is provided with a first housing 9. Several bolts 12 are installed on the outer wall of the first housing 9. One end of the bolt 12 passes through the first housing 9 and is connected to the outer wall of the second housing 10.

[0031] In use, the bolts 12 are used to connect the first housing 9 and the second housing 10 for installation.

[0032] A second housing 10 is installed at the end of the first housing 9 away from the U-shaped frame 8. A tripod 16 is provided inside the first housing 9 and the second housing 10. Equally spaced limiting seats 11 are provided inside the first housing 9 and the second housing 10 outside the tripod 16. Several micro motors 17 are installed on the inner wall of the tripod 16. A rotating shaft 18 is installed at the output end of the micro motor 17 through a coupling. The end of the rotating shaft 18 away from the micro motor 17 extends into the interior of the limiting seat 11 and is provided with a blade body 3. The end of the blade body 3 away from the micro motor 17 extends into the exterior of the limiting seat 11. The blade body 3 is movably connected to the limiting seat 11.

[0033] In this embodiment, the reducer 6 is first driven by the rotary drive 5, causing the reducer 6 to rotate slightly via the output shaft 7, which in turn drives the U-shaped frame 8 to rotate slightly outside the hollow positioning seat 1. This allows the U-shaped frame 8 to rotate accordingly via the connecting column 2, thereby adjusting the angle of several blade bodies 3 as a whole. Then, by starting the micro motor 17, the blade bodies 3 are driven to rotate via the rotating shaft 18. Due to the setting of the limiting seat 11, the movement amplitude of one end of the blade body 3 is limited, thereby enabling electric adjustment of the tilt angle of the blade body 3. Finally, by turning the lock... By tightening bolt 13 and bolt 12, the circular plate 14 can be removed from the outer wall of the first housing 9, and the second housing 10 can be removed from one end of the first housing 9. This makes it easier to clean and maintain the inner parts of the first housing 9 and the second housing 10. Then, by placing the hollow positioning seat 1 on the low-altitude aircraft and calibrating the positioning bolt 4 in the threaded hole reserved in the low-altitude aircraft, and then turning the positioning bolt 4 so that one end of the positioning bolt 4 passes through the hollow positioning seat 1 and is screwed into the threaded hole of the low-altitude aircraft, the hollow positioning seat 1 can be bolted and installed on the low-altitude aircraft, thus completing the use of the adjustment mechanism.

Claims

1. A propeller blade angle adjustment mechanism, characterized by: The system includes a hollow positioning base (1), inside which a reducer (6) is provided. Both ends of the reducer (6) are provided with output shafts (7). The end of the output shaft (7) away from the reducer (6) extends to the outside of the hollow positioning base (1) and is provided with a U-shaped frame (8). A connecting column (2) is installed on the inner wall of one side of the U-shaped frame (8). The end of the connecting column (2) away from the U-shaped frame (8) is provided with a first housing (9). The end of the first housing (9) away from the U-shaped frame (8) is provided with a second housing (10). Triangular frames are provided inside the first housing (9) and the second housing (10). (16) The first housing (9) and the second housing (10) on the outside of the tripod (16) are provided with equally spaced limiting seats (11). Several micro motors (17) are installed on the inner wall of the tripod (16). The output end of the micro motor (17) is connected to a rotating shaft (18) via a coupling. The end of the rotating shaft (18) away from the micro motor (17) extends into the interior of the limiting seat (11) and is provided with a blade body (3). The end of the blade body (3) away from the micro motor (17) extends into the exterior of the limiting seat (11). The blade body (3) is movably connected to the limiting seat (11).

2. A propeller blade angle adjustment mechanism according to claim 1, characterised in that: Positioning bolts (4) are installed at the corners of the outer wall of the hollow positioning seat (1), and one end of the positioning bolts (4) extends through to the outside of the hollow positioning seat (1).

3. A propeller blade angle adjustment mechanism according to claim 1, wherein: A rotary drive (5) is installed on the outer wall of the hollow positioning seat (1). One end of the rotary drive (5) extends into the interior of the hollow positioning seat (1) and is connected to the input shaft of the outer wall of the reducer (6).

4. The propeller blade angle adjustment mechanism according to claim 1, characterized in that: A circular plate (14) is provided on the outer wall of the first housing (9) outside the connecting column (2), and a column cylinder (15) is provided on the outer wall of the circular plate (14) outside the connecting column (2), and the column cylinder (15) is movably connected to the connecting column (2).

5. A propeller blade angle adjustment mechanism according to claim 1, wherein: A plurality of bolts (12) are installed on the outer wall of the first housing (9), one end of the bolts (12) penetrates the first housing (9) and is connected to the outer wall of the second housing (10).

6. A propeller blade angle adjustment mechanism according to claim 4, wherein: A number of locking bolts (13) are installed on the outer wall of the circular plate (14). One end of the locking bolt (13) passes through the circular plate (14) and is threadedly connected to the outer wall of the first housing (9).

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