Tilting mechanism with double self-locking rotors
By introducing the chute slider and universal ball limit sleeve structure into the rotor tilt mechanism, the instability problem of the rotor tilt mechanism during the airflow changes is solved, and the stability and service life of the fuselage are improved.
Patent Information
- Application Number
- CN202422607733.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-28
- Publication Date
- 2025-08-08
- Estimated Expiration
- 2034-10-28
AI Technical Summary
When the existing rotor tilt mechanism rotates for a long time, it is difficult to control the tilt angle, resulting in unstable fuselage.
The dual self-locking rotor tilt mechanism is adopted. By setting a slide chute and slider inside the connecting assembly, combining a universal ball and a limit sleeve, stable support and angle adjustment of the wing are achieved, springs and connecting rods provide support effects, and service life is improved through the low friction rotation of the universal ball.
It improves the stability and service life of the fuselage, ensures that the wings maintain a stable inclination angle under different airflow conditions, and reduces the heat generated by friction.
Smart Images
Figure CN223200274U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of rotor tilting, and more specifically, to a double self-locking rotor tilting mechanism. Background Art
[0002] A tilt-wing is a type of rotatable wing. Depending on the rotation mode, the aircraft has different flight characteristics. When the tilt-wing is in a vertical position, the aircraft can hover, fly sideways, fly backwards, take off and land vertically, etc. However, when the existing rotor tilt mechanism rotates for a long time, the tilt angle is difficult to control due to the different wind speeds encountered, which can easily cause the fuselage to become unstable. Utility Model Content
[0003] In order to overcome the deficiencies of the prior art, the utility model provides a dual self-locking rotor tilting mechanism, which has the advantage of improving the stability of the fuselage.
[0004] To achieve the above-mentioned purpose, the present invention provides the following technical solution: a dual self-locking rotor tilt mechanism, comprising a connecting shell, a motor fixedly mounted on the bottom of the connecting shell, a driving gear fixedly mounted on the output end of the motor, a rotating shaft rotatably connected to the inside of the connecting shell, a driven gear fixedly mounted on the outside of the rotating shaft, the driving gear and the driven gear are in meshing shape, a fixing ring fixedly mounted on the outside of the rotating shaft, and a fixing block fixedly mounted on the outside of the fixing ring.
[0005] As an optimal technical solution of the present invention, a connecting shaft is inserted into the interior of the fixed block, a rotating sleeve is sleeved on the outside of the connecting shaft, a fixed sleeve 1 is fixedly installed above the rotating sleeve, a limiting plate 1 is fixedly installed on the outside of the fixed sleeve 1, a spring is sleeved on the outside of the fixed sleeve 1, and a connecting rod is slidably connected to the interior of the fixed sleeve 1.
[0006] As an optimal technical solution of the present invention, a ball sleeve is fixedly installed above the rotating shaft, a universal ball is provided inside the ball sleeve, a limiting sleeve is sleeved on the outer side of the universal ball, the limiting sleeve is located above the ball sleeve, and the limiting sleeve and the ball sleeve are connected by bolts.
[0007] As an optimal technical solution of the present invention, a connecting block is fixedly installed above the universal ball, a wing and a connecting component are fixedly installed on the outside of the connecting block, a slide groove is provided inside the connecting component, a slider is slidably connected inside the slide groove, a limiting plate 2 is fixedly installed on the bottom of the slider, and a fixing sleeve 2 is fixedly installed on the bottom of the limiting plate 2.
[0008] As a preferred technical solution of the present utility model, there are four fixed blocks, which are respectively located on the left and right sides of the fixed ring; there are two connecting shafts, which are respectively located inside the four fixed blocks; there are two rotating sleeves and two fixed sleeves, which are respectively rotatably connected to the two connecting shafts.
[0009] As a preferred technical solution of the present invention, the end of the rotating shaft away from the ball sleeve is fixedly connected to the fuselage, so that the direction and position of the rotating shaft are fixed. There are two wings, and both wings are located above the connecting shell.
[0010] Compared with the prior art, the beneficial effects of the present invention are as follows:
[0011] 1. The utility model has a sliding groove inside the connecting component, a slider is slidably connected inside the sliding groove, and a fixed sleeve 2 is fixedly installed on the bottom of the slider, a connecting rod is slidably connected inside the fixed sleeve 2, and a spring is sleeved on the outside of the connecting rod. When the connecting component drives the wing to tilt, the slider will slide outward inside the slider, and the connecting rod will contract inside the fixed sleeve 2. Therefore, when tilting, it can provide a certain supporting effect on the connecting component to maintain overall stability.
[0012] 2. The utility model provides a universal ball inside the ball sleeve, and a limit sleeve is sleeved on the outside of the universal ball. The limit sleeve is located above the ball sleeve and is connected to the ball sleeve by bolts. When the wing needs to tilt, the universal ball will rotate inside the limit sleeve, so that the universal ball drives the connecting block to tilt. At the same time, since the universal ball is spherical, the friction generated by the rotation inside the limit sleeve is small, so the temperature generated is small, which improves the overall service life. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 This is a schematic diagram of the overall structure of the utility model;
[0014] Figure 2 For this utility model Figure 1 A magnified schematic diagram of the structure at A;
[0015] Figure 3 This is a schematic diagram of the wing structure of the utility model;
[0016] Figure 4 For this utility model Figure 3 A magnified schematic diagram of the structure at B;
[0017] Figure 5 This is a schematic diagram of the connecting shaft structure of the utility model.
[0018] In the figure: 1. Connecting housing; 2. Motor; 3. Driving gear; 4. Rotating shaft; 5. Driven gear; 6. Fixed ring; 7. Fixed block; 8. Connecting shaft; 9. Rotating sleeve; 10. Fixed sleeve; 11. Limiting plate 1; 12. Spring; 13. Connecting rod; 14. Ball sleeve; 15. Universal ball; 16. Limiting sleeve; 17. Connecting block; 18. Wing; 19. Connecting assembly; 20. Slide; 21. Slider; 22. Limiting plate 2; 23. Fixed sleeve 2. DETAILED DESCRIPTION
[0019] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.
[0020] like Figures 1 to 5 As shown, the utility model provides a dual self-locking rotor tilt mechanism, including a connecting shell 1, a motor 2 is fixedly installed on the bottom of the connecting shell 1, a driving gear 3 is fixedly installed on the output end of the motor 2, a rotating shaft 4 is rotatably connected to the inside of the connecting shell 1, a driven gear 5 is fixedly installed on the outside of the rotating shaft 4, the driving gear 3 and the driven gear 5 are in meshing shape, a fixing ring 6 is fixedly installed on the outside of the rotating shaft 4, and a fixing block 7 is fixedly installed on the outside of the fixing ring 6.
[0021] The starting motor 2 drives the driving gear 3 to rotate through the output end, so that the driving gear 3 is engaged with the driven gear 5, thereby driving the rotating shaft 4 to rotate rapidly, achieving the effect of driving the fuselage to rise and fall through high-speed rotation.
[0022] Among them, the interior of the fixed block 7 is plugged with a connecting shaft 8, the outer side of the connecting shaft 8 is sleeved with a rotating sleeve 9, a fixed sleeve 10 is fixedly installed above the rotating sleeve 9, a limiting plate 11 is fixedly installed on the outer side of the fixed sleeve 10, a spring 12 is sleeved on the outer side of the fixed sleeve 10, and the interior of the fixed sleeve 10 is slidably connected to a connecting rod 13.
[0023] The spring 12 is located on the outside of the connecting rod 13. When the wing 18 tilts, the connecting rod 13 is pressed down, causing the connecting rod 13 to contract inside the spring 12, thereby achieving the effect of tilting while maintaining the stability of the wing 18.
[0024] Among them, a ball sleeve 14 is fixedly installed above the rotating shaft 4, and a universal ball 15 is provided inside the ball sleeve 14. The outer side of the universal ball 15 is sleeved with a limit sleeve 16. The limit sleeve 16 is located above the ball sleeve 14, and the limit sleeve 16 and the ball sleeve 14 are connected by bolts.
[0025] The inner diameter of the ball sleeve 14 is smaller than the diameter at the center of the universal ball 15. When the universal ball 15 rotates inside the ball sleeve 14, the surrounding area will be limited by the limiting sleeve 16, thereby ensuring the overall stability of the universal ball 15 while ensuring the rotation of the universal ball 15.
[0026] Among them, a connecting block 17 is fixedly installed above the universal ball 15, and a wing 18 and a connecting component 19 are fixedly installed on the outside of the connecting block 17. A slide groove 20 is opened inside the connecting component 19, and a slider 21 is slidably connected inside the slide groove 20. A limit plate 22 is fixedly installed at the bottom of the slider 21, and a fixed sleeve 23 is fixedly installed at the bottom of the limit plate 22.
[0027] The limiting plate 22 is located above the spring 12, and the fixing sleeve 23 is located inside the connecting rod 13 and inside the spring 12. At the same time, the fixing sleeve 23 is located above the fixing sleeve 10. The main function of the limiting plate 22 is to limit the spring 12 to prevent the spring 12 from providing more force under the action of elastic force, causing the connecting component 19 to tilt upward.
[0028] Among them, there are four fixed blocks 7, which are respectively located on the left and right sides of the fixed ring 6; there are two connecting shafts 8, which are respectively located inside the four fixed blocks 7; there are two rotating sleeves 9 and two fixed sleeves 10, and the two rotating sleeves 9 are respectively connected to the two connecting shafts 8 for rotation.
[0029] When the wing 18 needs to adjust its direction and tilt according to the airflow, the connecting component 19 will be pressed downward, so that the slider 21 will slide inside the slide groove 20, causing the spring 12, the connecting rod 13 and the fixing sleeve 23 to tilt outward, thereby achieving a certain supporting effect on the connecting component 19. At the same time, when the wing 18 does not need to move, the spring 12 provides elastic force to reset the connecting component 19 and keep it parallel to the wing 18.
[0030] Among them, one end of the rotating shaft 4 away from the ball sleeve 14 is fixedly connected to the fuselage, so that the direction and position of the rotating shaft 4 are fixed. There are two wings 18, and the two wings 18 are both located above the connecting shell 1.
[0031] The main function of the two wings 18 is to generate an upward force by rotating at high speed, so that the fuselage can be lifted up easily, and at the same time, to realize forward and backward instructions by adjusting the tilt angle.
[0032] The working principle and use process of this utility model:
[0033] First, the motor 2 is started to drive the driving gear 3 to rotate through the output end, so that the driving gear 3 is engaged with the driven gear 5, thereby driving the rotating shaft 4 to rotate at high speed;
[0034] At the same time, since a fixing ring 6 is fixedly installed on the outside of the rotating shaft 4, a fixing block 7 is fixedly installed on the outside of the fixing ring 6, a connecting shaft 8 is inserted into the inside of the fixing block 7, a rotating sleeve 9 is sleeved on the outside of the connecting shaft 8, a fixing sleeve 10 and a limiting plate 11 are fixedly installed above the rotating sleeve 9, and a spring 12 is fixedly sleeved on the outside of the fixing sleeve 10 and the limiting plate 11, and a slider 21 is fixedly installed above the spring 12. The slider 21 is located inside the connecting assembly 19. Therefore, when the rotating shaft 4 rotates, it will drive the connecting assembly 19 to rotate at high speed, and at the same time, the wing 18 will rotate, so as to achieve the effect of driving the fuselage to rise, move forward and backward, and land;
[0035] Finally, when the inclination angle of the wing 18 needs to be adjusted, the universal ball 15 will rotate in the limit sleeve 16, so that the angle of the connecting block 17 is tilted, thereby adjusting the inclination of the wing 18. At the same time, since the universal ball 15 is spherical, the friction generated by the rotation inside the limit sleeve 16 is small, so the temperature generated is small, which improves the overall service life.
[0036] It should be noted that, in this document, relational terms such as first and second, etc., are used only 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 terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.
[0037] Although the embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. A dual self-locking rotor tilt mechanism, comprising a connecting housing (1), characterized in that: A motor (2) is fixedly mounted on the bottom of the connecting housing (1), a driving gear (3) is fixedly mounted on the output end of the motor (2), a rotating shaft (4) is rotatably connected to the interior of the connecting housing (1), a driven gear (5) is fixedly mounted on the outside of the rotating shaft (4), the driving gear (3) and the driven gear (5) are in meshing engagement, a fixing ring (6) is fixedly mounted on the outside of the rotating shaft (4), and a fixing block (7) is fixedly mounted on the outside of the fixing ring (6).
2. The dual self-locking rotor tilt mechanism according to claim 1, characterized in that: A connecting shaft (8) is inserted into the interior of the fixed block (7), a rotating sleeve (9) is sleeved on the outside of the connecting shaft (8), a fixed sleeve (10) is fixedly installed above the rotating sleeve (9), a limiting plate (11) is fixedly installed on the outside of the fixed sleeve (10), a spring (12) is sleeved on the outside of the fixed sleeve (10), and a connecting rod (13) is slidably connected to the interior of the fixed sleeve (10).
3. The dual self-locking rotor tilt mechanism according to claim 1, characterized in that: A ball sleeve (14) is fixedly mounted above the rotating shaft (4), a universal ball (15) is provided inside the ball sleeve (14), a limiting sleeve (16) is sleeved on the outer side of the universal ball (15), the limiting sleeve (16) is located above the ball sleeve (14), and the limiting sleeve (16) and the ball sleeve (14) are connected by bolts.
4. The dual self-locking rotor tilt mechanism according to claim 3, characterized in that: A connecting block (17) is fixedly installed above the universal ball (15), a wing (18) and a connecting assembly (19) are fixedly installed on the outside of the connecting block (17), a sliding groove (20) is provided inside the connecting assembly (19), a slider (21) is slidably connected inside the sliding groove (20), a limiting plate 2 (22) is fixedly installed at the bottom of the slider (21), and a fixing sleeve 2 (23) is fixedly installed at the bottom of the limiting plate 2 (22).
5. The dual self-locking rotor tilt mechanism according to claim 2, characterized in that: There are four fixed blocks (7), and the four fixed blocks (7) are respectively located on the left and right sides of the fixed ring (6). There are two connecting shafts (8), and the two connecting shafts (8) are respectively located inside the four fixed blocks (7). There are two rotating sleeves (9) and two fixed sleeves (10), and the two rotating sleeves (9) are respectively connected to the two connecting shafts (8) for rotation.
6. The dual self-locking rotor tilt mechanism according to claim 4, characterized in that: One end of the rotating shaft (4) away from the ball sleeve (14) is fixedly connected to the fuselage, thereby fixing the direction and position of the rotating shaft (4). There are two wings (18), and both wings (18) are located above the connecting shell (1).