Tilting mechanism of electric vertical take-off and landing aircraft

Abstract

The utility model relates to the technical field of electric vertical take-off and landing aircrafts, and discloses a tilting mechanism of an electric vertical take-off and landing aircraft, which comprises a support frame, the rear side of the support frame is fixedly connected with a driving motor, an output shaft of the driving motor is fixedly sleeved with a rotating plate, the front side of the rotating plate is fixedly connected with a rotating disc, and the rotating disc is fixedly connected with a motor. The front side of the supporting frame is fixedly connected with an air cylinder, the front side of the supporting frame is fixedly connected with a mounting plate, the left side of the mounting plate is fixedly connected with a limiting spring, the left side of the limiting spring is fixedly connected with a limiting insertion rod, and the right side of the limiting insertion rod is fixedly connected with a movable rod. Therefore, after the tilting angle of the rotating plate is adjusted, the rotating plate can be locked by inserting the limiting insertion rod into the inner cavity of the rotating disc, and the driving motor does not need to continuously output power to stabilize the rotating plate.

Description

Technical Field

[0001] The utility model relates to the technical field of electric vertical take-off and landing aircraft, and more specifically, the utility model relates to a tilting mechanism of an electric vertical take-off and landing aircraft. Background Technique

[0002] The electric vertical take-off and landing aircraft is abbreviated as eVTOL. During the flight or take-off of its propellers, a tilting mechanism is required to tilt the propellers of the electric vertical take-off and landing aircraft, thereby adjusting the angles of the propellers. However, after tilting, electrical components are often needed to fix the tilted angles, but this may lead to the continuous operation of the electrical components, which is not conducive to energy conservation and causes energy waste. Content of the Utility Model

[0003] In order to overcome the deficiencies of the prior art, the utility model provides a tilting mechanism of an electric vertical take-off and landing aircraft, which has the advantage of energy conservation.

[0004] To achieve the above object, the utility model provides the following technical solution: A tilting mechanism of an electric vertical take-off and landing aircraft, including a support frame, a driving motor is fixedly connected to the rear side of the support frame, a rotating plate is fixedly sleeved on the output shaft of the driving motor, a rotating disc is fixedly connected to the front side of the rotating plate, a cylinder is fixedly connected to the front side of the support frame, a mounting plate is fixedly connected to the front side of the support frame, a limiting spring is fixedly connected to the left side of the mounting plate, a limiting insertion rod is fixedly connected to the left side of the limiting spring, and a movable rod is fixedly connected to the right side of the limiting insertion rod.

[0005] As a preferred technical solution of the utility model, a mounting frame is fixedly connected to the outside of the support frame, a moving ring is fixedly connected to the front side of the mounting frame, a guiding rod is fixedly connected to the inner cavity of the moving ring, a storage bin is fixedly connected to the right side of the guiding rod, a servo motor is fixedly connected to the inner cavity of the storage bin, a threaded rod is fixedly sleeved on the output shaft of the servo motor, and a meshing ring is meshed with the surface of the threaded rod.

[0006] As a preferred technical solution of the utility model, a propeller is fixedly connected to the left side of the rotating plate, and the rotating plate is movably sleeved in the inner cavity of the support frame.

[0007] As a preferred technical solution of the utility model, a plurality of limiting grooves are formed in the middle of the rotating disc, the limiting insertion rod is inserted into the limiting grooves, and the rotating disc passes through the support frame and is fixedly connected to the rotating plate.

[0008] As a preferred technical solution of the utility model, the movable rod is located at the center of the inner cavity of the limiting spring, a circular hole is formed in the middle of the mounting plate, and the right side of the movable rod is movably sleeved in the circular hole.

[0009] As a preferred technical solution of the present utility model, there are two moving rings and two guiding rods. The two moving rings are respectively fixedly connected to the rear side and the bottom of the support frame, and the two guiding rods are respectively fixedly connected to the rear side and the bottom of the inner cavity of the storage bin.

[0010] As a preferred technical solution of the present utility model, the top end of the mounting frame is located above the rotating disc and the driving motor. A placement groove is provided on the right side of the storage bin, and the servo motor is fixedly connected to the inner cavity of the placement groove.

[0011] Compared with the prior art, the beneficial effects of the present utility model are as follows:

[0012] 1. By starting the driving motor to drive the rotating plate to operate, the tilting angle of the propeller is adjusted. When the rotating plate rotates to adjust the tilting angle of the propeller, the rotating disc is driven to rotate. Then, the air cylinder is started to operate, and the output shaft of the air cylinder squeezes the movable rod. The movable rod drives the limit insertion rod to insert into the inner cavity of the rotating disc, thereby locking the rotation angle of the rotating disc. Then, the air cylinder stops operating. When the angle of the propeller needs to be adjusted again, the air cylinder is started to make its output shaft leave the movable rod. The limit insertion rod resets under the pulling force of the limit spring, so that the limit insertion rod leaves the inner cavity of the rotating disc, releasing the limit lock of the rotating plate. Thus, after adjusting the tilting angle of the rotating plate, the rotating plate can be locked by inserting the limit insertion rod into the inner cavity of the rotating disc, so that it is no longer necessary for the driving motor to continuously output power to stabilize the rotating plate.

[0013] 2. After the angle of the propeller is adjusted to the horizontal state, the servo motor is started to drive the threaded rod to rotate. Then, the rotation of the threaded rod drives the engagement ring to move along the axis direction of the threaded rod, thereby driving the mounting frame to move along the axis directions of the guiding rod and the threaded rod, and further driving the support frame, the driving motor, and the rotating plate to be received into the inner cavity of the storage bin, thus reducing the external volume of the overall structure and improving the aerodynamic efficiency during the cruising stage. Description of the Drawings

[0014] Figure 1 It is a schematic structural diagram of the present utility model;

[0015] Figure 2 It is a schematic connection diagram of the threaded rod of the structure of the present utility model;

[0016] Figure 3 It is a schematic connection diagram of the rotating disc of the structure of the present utility model;

[0017] Figure 4 It is a schematic connection diagram of the rotating plate of the structure of the present utility model;

[0018] Figure 5This is a schematic diagram of the connection of the structural limit insertion rod of the present utility model.

[0019] In the figure: 1, support frame; 2, drive motor; 3, rotating plate; 4, propeller; 5, rotating disk; 6, cylinder; 7, mounting plate; 8, limit spring; 9, limit insertion rod; 10, movable rod; 11, mounting frame; 12, moving ring; 13, guide rod; 14, storage bin; 15, servo motor; 16, threaded rod; 17, meshing ring. Specific embodiments

[0020] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

[0021] As Figures 1 to 5 shown, the present utility model provides a tilting mechanism for an electric vertical take-off and landing aircraft, including a support frame 1. A drive motor 2 is fixedly connected to the rear side of the support frame 1. The output shaft of the drive motor 2 is fixedly sleeved with a rotating plate 3. A rotating disk 5 is fixedly connected to the front side of the rotating plate 3. A cylinder 6 is fixedly connected to the front side of the support frame 1. A mounting plate 7 is fixedly connected to the front side of the support frame 1. A limit spring 8 is fixedly connected to the left side of the mounting plate 7. A limit insertion rod 9 is fixedly connected to the left side of the limit spring 8. A movable rod 10 is fixedly connected to the right side of the limit insertion rod 9;

[0022] By starting the drive motor 2 to drive the rotating plate 3 to operate, the tilting angle of the propeller 4 is adjusted accordingly. When the rotating plate 3 rotates to adjust the tilting angle of the propeller 4, the rotating disk 5 is driven to rotate. Then, the cylinder 6 is started to operate. The output shaft of the cylinder 6 presses the movable rod 10. The movable rod 10 drives the limit insertion rod 9 to insert into the inner cavity of the rotating disk 5, thereby locking the rotating angle of the rotating disk 5. Then, the cylinder 6 stops operating. When the angle of the propeller 4 needs to be adjusted again, the cylinder 6 is started to make its output shaft leave the movable rod 10. The limit insertion rod 9 is reset under the pulling force of the limit spring 8, so that the limit insertion rod 9 leaves the inner cavity of the rotating disk 5, releasing the limit lock on the rotating plate 3. Thus, after adjusting the tilting angle of the rotating plate 3, the rotating plate 3 can be locked by inserting the limit insertion rod 9 into the inner cavity of the rotating disk 5, and there is no need for the drive motor 2 to continuously output power to stabilize the rotating plate 3.

[0023] Among them, an installation frame 11 is fixedly connected to the outer side of the support frame 1. A moving ring 12 is fixedly connected to the front side of the installation frame 11. A guide rod 13 is fixedly connected to the inner cavity of the moving ring 12. A storage bin 14 is fixedly connected to the right side of the guide rod 13. A servo motor 15 is fixedly connected to the inner cavity of the storage bin 14. A threaded rod 16 is fixedly sleeved on the output shaft of the servo motor 15. A meshing ring 17 is meshed with the surface of the threaded rod 16;

[0024] After the angle of the propeller 4 is adjusted to a horizontal state, the servo motor 15 is started to drive the threaded rod 16 to rotate. Then, the rotation of the threaded rod 16 drives the meshing ring 17 to move along the axis direction of the threaded rod 16, thereby driving the installation frame 11 to move along the axis directions of the guide rod 13 and the threaded rod 16, and further driving the support frame 1, the drive motor 2, and the rotating plate 3 to be stored in the inner cavity of the storage bin 14, thus reducing the external volume of the overall structure and improving the aerodynamic efficiency during the cruise stage.

[0025] Among them, a propeller 4 is fixedly connected to the left side of the rotating plate 3. The rotating plate 3 is movably sleeved in the inner cavity of the support frame 1;

[0026] Through the propeller 4 on the left side of the rotating plate 3, the entire aircraft is driven to fly through the high-speed rotation of the propeller 4, and the tilt angle of the propeller 4 can be adjusted by adjusting the angle of the rotating plate 3.

[0027] Among them, a plurality of limiting grooves are formed in the middle of the rotating disc 5. The limiting insertion rod 9 is inserted into the limiting groove. The rotating disc 5 passes through the support frame 1 and is fixedly connected to the rotating plate 3;

[0028] Through the arrangement of the limiting grooves, after the movable rod 10 is squeezed by the output shaft of the air cylinder 6, the limiting insertion rod 9 can be driven to insert into the inner cavity of the limiting groove, thereby limiting and fixing the position of the rotating disc 5, and avoiding the situation that the output shaft of the air cylinder 6 is directly inserted into the inner cavity of the rotating disc 5, resulting in damage to the internal components due to the force of the rotating disc 5 rotating on the output shaft of the air cylinder 6. By using components such as the mounting plate 7, the limiting spring 8, the limiting insertion rod 9, and the movable rod 10, the failure rate is reduced, and the maintenance and repair cost is also reduced.

[0029] Among them, the movable rod 10 is located at the center of the inner cavity of the limiting spring 8. A circular hole is formed in the middle of the mounting plate 7. The right side of the movable rod 10 is movably sleeved in the circular hole;

[0030] By the movable rod 10 being located at the center of the inner cavity of the limiting spring 8 and the movable rod 10 being movably sleeved in the circular hole, the limiting insertion rod 9 can be positioned and guided through the movable rod 10, so that the limiting spring 8 is more stable when driving the limiting insertion rod 9 to reset and leave the inner cavity of the rotating disc 5.

[0031] Among them, there are two moving rings 12 and two guide rods 13. The two moving rings 12 are respectively fixedly connected to the rear side and the bottom of the support frame 1, and the two guide rods 13 are respectively fixedly connected to the rear side and the bottom of the inner cavity of the storage bin 14;

[0032] Through the arrangement of the two moving rings 12 and the two guide rods 13, the guide rod 13 can support and guide the rear side and the bottom of the mounting frame 11, so as to avoid the situation that the mounting frame 11 is offset during the process of the threaded rod 16 rotating to drive the mounting frame 11 to move, and improve the stability of the mounting frame 11 during movement.

[0033] Among them, the top end of the mounting frame 11 is located above the rotating disk 5 and the driving motor 2. A placement groove is opened on the right side of the storage bin 14, and the servo motor 15 is fixedly connected to the inner cavity of the placement groove;

[0034] Since the top end of the mounting frame 11 is located above the rotating disk 5 and the driving motor 2, the mounting frame 11 can protect the upper parts of the driving motor 2 and the rotating disk 5, preventing some rainwater and the like from affecting the normal use of the driving motor 2 and the rotating disk 5. Through the arrangement of the placement groove, the servo motor 15 can be stored.

[0035] The working principle and usage process of the present utility model: By starting the driving motor 2 to drive the rotating plate 3 to rotate, and then through the rotation of the rotating plate 3 to drive the propeller 4 to move, so as to adjust the angle of the propeller 4. After the adjustment is completed, start the cylinder 6 to operate. The cylinder 6 squeezes the movable rod 10, and the movable rod 10 drives the limit insertion rod 9 to move towards the rotating disk 5, so that the limit insertion rod 9 is inserted into the inner cavity of the rotating disk 5 to lock the rotating disk 5. When the angle needs to be adjusted again, start the cylinder 6 to move away from the movable rod 10. At this time, the limit spring 8 pulls the limit insertion rod 9 to leave the inner cavity of the rotating disk 5, so as to release the lock on the rotating disk 5, and further release the lock on the rotating plate 3, enabling the rotating plate 3 to rotate again;

[0036] When the angle of the propeller 4 is adjusted to the horizontal state, the servo motor 15 can be started to drive the threaded rod 16 to rotate. Through the rotation of the threaded rod 16, the engaging ring 17 engaged with it moves along the axis direction of the threaded rod 16, and further drives the mounting frame 11 to move along the axis directions of the guide rod 13 and the threaded rod 16 into the inner cavity of the storage bin 14 for storage;

[0037] Then start the propeller 4 to rotate to drive the entire electric vertical take-off and landing aircraft to operate.

[0038] It should be noted that in this text, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variation thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements not only includes those elements, but also includes other elements not expressly listed, or elements inherent to such process, method, article or device.

[0039] Although embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A tilting mechanism for an electric vertical take-off and landing aircraft, comprising a support frame (1), characterized in that: A driving motor (2) is fixedly connected to the rear side of the support frame (1). A rotating plate (3) is fixedly sleeved on the output shaft of the driving motor (2). A rotating disc (5) is fixedly connected to the front side of the rotating plate (3). A cylinder (6) is fixedly connected to the front side of the support frame (1). An installation plate (7) is fixedly connected to the front side of the support frame (1). A limiting spring (8) is fixedly connected to the left side of the installation plate (7). A limiting insertion rod (9) is fixedly connected to the left side of the limiting spring (8). A movable rod (10) is fixedly connected to the right side of the limiting insertion rod (9).

2. The tilting mechanism of an electric vertical take-off and landing aircraft according to claim 1, characterized in that: An installation frame (11) is fixedly connected to the outer side of the support frame (1). A moving ring (12) is fixedly connected to the front side of the installation frame (11). A guiding rod (13) is fixedly connected to the inner cavity of the moving ring (12). A storage bin (14) is fixedly connected to the right side of the guiding rod (13). A servo motor (15) is fixedly connected to the inner cavity of the storage bin (14). A threaded rod (16) is fixedly sleeved on the output shaft of the servo motor (15). A meshing ring (17) is meshed on the surface of the threaded rod (16).

3. The tilting mechanism of an electric vertical take-off and landing aircraft according to claim 1, characterized in that: A propeller (4) is fixedly connected to the left side of the rotating plate (3). The rotating plate (3) is movably sleeved in the inner cavity of the support frame (1).

4. The tilting mechanism of an electric vertical take-off and landing aircraft according to claim 1, characterized in that: A plurality of limiting grooves are formed in the middle of the rotating disc (5). The limiting insertion rod (9) is inserted into the limiting grooves. The rotating disc (5) passes through the support frame (1) and is fixedly connected to the rotating plate (3).

5. The tilting mechanism of an electric vertical takeoff and landing aircraft according to claim 1, characterized in that: The movable rod (10) is located at the center of the inner cavity of the limiting spring (8). A round hole is formed in the middle of the installation plate (7). The right side of the movable rod (10) is movably sleeved in the round hole.

6. The tilting mechanism of an electric vertical take-off and landing aircraft according to claim 2, characterized in that: Both the moving ring (12) and the guiding rod (13) are provided with two. The two moving rings (12) are respectively fixedly connected to the rear side and the bottom of the support frame (1). The two guiding rods (13) are respectively fixedly connected to the rear side and the bottom of the inner cavity of the storage bin (14).

7. The tilting mechanism of an electric vertical take-off and landing aircraft according to claim 2, characterized in that: The top end of the installation frame (11) is located above the rotating disc (5) and the driving motor (2). A placing groove is formed in the right side of the storage bin (14). The servo motor (15) is fixedly connected to the inner cavity of the placing groove.

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