Propeller and unmanned aerial vehicle
By introducing detachable pitch blocks and mechanical adjustment devices into the drone propellers, the problem of insufficient thrust in high-altitude areas of drones has been solved, achieving simple structure, convenient maintenance and efficient flight.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- SHENZHEN HOBBYWING TECH CO LTD
- Filing Date
- 2025-12-18
- Publication Date
- 2026-04-14
AI Technical Summary
Existing drone pitch designs suffer from complex structures, difficult maintenance, or insufficient thrust at high altitudes. Existing electric variable pitch systems are bulky and unreliable, while fixed pitch blades struggle to provide sufficient lift at high altitudes.
A propeller is provided in which a multi-angle pitch block is detachably installed in the pitch control chamber, allowing the user to manually adjust the blade pitch angle. Combined with a mechanical adjustment device, it eliminates the need for a servo drive mechanism and adapts to different flight scenarios.
It enables efficient flight of drones in different altitude environments, reduces maintenance costs and motor power requirements, and improves flight efficiency and endurance.
Smart Images
Figure CN121849409A_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a propeller and a UAV. Background Technology
[0002] The pitch angle of a drone propeller blade refers to the angle between the blade chord and the plane of rotation. This parameter directly determines the angle at which the blade cuts into the air, thus affecting the drone's thrust output, flight efficiency, and payload capacity. A smaller pitch angle is suitable for low-load cruise and has lower energy consumption; a larger pitch angle can provide stronger thrust and is suitable for heavy-load or rapid climb scenarios. Therefore, the setting of the pitch angle is crucial to the drone's flight performance.
[0003] In implementing the embodiments of this application, the inventors discovered that there are currently two main pitch design schemes in the prior art. The first is an electric variable pitch system, which can achieve rapid response adjustment of the blade pitch. However, due to the need for additional servo drive mechanism, the overall size is large and the structure is complex. Once the electric variable pitch system fails, the maintenance is difficult, increasing the cost of use and maintenance cycle. The second is a fixed pitch blade, which has a simple structure and high reliability. However, the blade pitch is fixed after leaving the factory. When the UAV operates in plateau or high-altitude areas, due to the decrease in air density, the fixed pitch blade is difficult to generate sufficient lift. It is necessary to increase the speed of the drive system to compensate for the insufficient thrust. This places higher demands on the motor power and heat dissipation performance, and also reduces flight efficiency and endurance. Summary of the Invention
[0004] The main technical problem solved by the embodiments of this application is to provide a propeller with an adjustment device that allows manual adjustment of the propeller blade pitch according to user needs. This allows users to change the installation angle (pitch) of the propeller blades by replacing or rotating the adjustment block without replacing the blades, in order to adapt to different flight scenarios and performance requirements.
[0005] To solve the above-mentioned technical problems, one technical solution adopted in this application embodiment is: providing a propeller, including a propeller clamp assembly, an adjustment device, a drive device, and a blade body. The adjustment device includes a first adjustment component, which is rotatably connected to one end of the propeller clamp assembly. The first adjustment component includes a first pitch chamber, a first pitch block, a first pitch shaft, and a first blade fixing member. The first pitch chamber has a first pitch chamber compartment. The first pitch block is detachably disposed in the first pitch chamber compartment. The first pitch block has multiple first abutment portions with different preset angles. One end of the first pitch shaft extends into the first pitch chamber compartment and abuts against one of the first abutment portions. The other end of the first pitch shaft passes through the first pitch chamber and is connected to the first blade fixing member. The drive device and the adjustment device are fixed to the drive device. The blade body is fixedly connected to the adjustment device.
[0006] Optionally, the first adjusting block has a polyhedral structure, and multiple first abutting parts are respectively disposed on different sides of the first adjusting block. Each first abutting part is an inclined groove. The first adjusting assembly also includes a first adjusting chamber cover plate and a first fastener. The first adjusting chamber cover plate covers the opening of the first adjusting chamber compartment, and the first fastener passes through the first adjusting chamber cover plate and the first adjusting block in sequence and is fixed to the first adjusting chamber.
[0007] Optionally, the first adjustable gap chamber is further provided with a first outlet hole communicating with the first adjustable gap chamber chamber, the first adjustable gap shaft passes through the first outlet hole, the first adjustable gap shaft is provided with a first abutting limiting platform, the first abutting limiting platform is located in the first adjustable gap chamber chamber and is embedded in the inclined groove and abuts against the first abutting part.
[0008] Optionally, the blade body includes a first blade, and the first blade fixing component includes a first blade fixing upper plate, a first blade fixing lower plate, and a first blade fixing shaft. The first blade fixing upper plate and the first blade fixing lower plate are both sleeved on the first pitch adjusting shaft. The first blade is sandwiched between the first blade fixing upper plate and the first blade fixing lower plate. The first blade fixing shaft passes through the first blade fixing upper plate, the first blade, and the first blade fixing lower plate in sequence and is fixedly connected.
[0009] Optionally, the first blade fixing upper plate is provided with a first upper plate anti-rotation groove, the first blade fixing lower plate is provided with a first lower plate anti-rotation groove, and the first pitch shaft is also provided with a first anti-rotation limiting platform, which is respectively engaged with the first upper plate anti-rotation groove and the first lower plate anti-rotation groove.
[0010] Optionally, the first blade fixing upper plate is further provided with a first upper plate rotation groove, the first blade fixing lower plate is further provided with a first lower plate rotation groove, and the first pitch shaft is further provided with a first rotating ring, the first rotating ring being respectively engaged with the first upper plate rotation groove and the first lower plate rotation groove.
[0011] Optionally, the propeller clamp assembly includes a propeller clamp base, a propeller clamp top cover, a first rotating shaft, and a first rotating shaft fastener. The propeller clamp base is sleeved on the first rotating shaft, the first pitch adjustment chamber is rotatably sleeved on one end of the first rotating shaft, the propeller clamp top cover is placed on the propeller clamp base, and the first rotating shaft fastener passes through the propeller clamp top cover and the propeller clamp base in sequence and is fixedly connected to the first rotating shaft.
[0012] Optionally, the propeller clamp assembly further includes a wear-resistant washer and a wear-resistant bushing. One end of the first pitch chamber is provided with a first pitch chamber rotation groove. The wear-resistant bushing is embedded in the first pitch chamber rotation groove. The first pitch chamber is rotatably mounted on the rotating shaft through the wear-resistant bushing. The wear-resistant washer is disposed between the first pitch chamber and the propeller clamp base.
[0013] Optionally, the adjustment device further includes a second adjustment component, which is rotatably connected to the other end of the propeller clamp assembly. The propeller body also includes a second propeller blade. The second adjustment component includes a second pitch chamber, a second pitch block, a second pitch shaft, and a second propeller blade fixing member. The second pitch chamber has a second pitch chamber compartment. The second pitch block is detachably disposed in the second pitch chamber compartment. The second pitch block has multiple second abutment portions with different preset angles. One end of the second pitch shaft extends into the second pitch chamber compartment and abuts against one of the second abutment portions. The other end of the second pitch shaft passes through the second pitch chamber and is connected to the second propeller blade fixing member. The second propeller blade is fixedly connected to the second propeller blade fixing member.
[0014] To solve the above-mentioned technical problems, another technical solution adopted in this application embodiment is to provide a drone that includes any of the above-mentioned propellers.
[0015] This application provides a propeller with a first pitch control block detachably installed inside a first pitch control chamber. The first pitch control block has multiple first abutment parts with different preset angles. A first pitch control shaft abuts against one of the first abutment parts. Users can change the pitch angle of the propeller blades by replacing the abutment parts that abut the first pitch control block against the first pitch control shaft, thereby adapting to the needs of different altitude environments and flight scenarios. Compared with electric variable pitch systems, the propeller in this application does not require a servo drive mechanism. The overall structure is simple and compact, small in size and light in weight, and there is no risk of electrical component failure. It is easy to maintain and highly reliable. Compared with fixed pitch propeller blades, the propeller pitch can be manually adjusted according to actual usage needs. When the UAV operates in plateau or high-altitude areas, a larger pitch angle can be selected to obtain sufficient lift without compensating by increasing the motor speed. This reduces the performance requirements of the drive system and improves flight efficiency and endurance. Attached Figure Description
[0016] To more clearly illustrate the technical solutions in the specific embodiments of this application or the prior art, the accompanying drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. In all the drawings, similar elements or parts are generally identified by similar reference numerals. In the drawings, the elements or parts are not necessarily drawn to scale.
[0017] Figure 1 This is a schematic diagram of the propeller in an embodiment of this application; Figure 2 This is a top view of the propeller in an embodiment of this application; Figure 3 This is an exploded view of a portion of the propeller structure according to an embodiment of this application; Figure 4 This is another exploded view of a portion of the propeller structure in an embodiment of this application; Figure 5 This is a schematic diagram of the first controllable block of the propeller in an embodiment of this application; Figure 6 This is a schematic diagram of various angles of the first inclined portion of the propeller in an embodiment of this application; Figure 7 This is a partial structural schematic diagram of the propeller according to an embodiment of this application; Figure 8 This is a schematic diagram of the first pitch control chamber of the propeller in an embodiment of this application; Figure 9 This is a schematic diagram of the upper plate fixing the first blade of the propeller in an embodiment of this application; Figure 10 This is a schematic diagram of the first blade fixing lower plate of the propeller in an embodiment of this application; Figure 11 This is a schematic diagram of the first pitch control shaft of the propeller in an embodiment of this application. Detailed Implementation
[0018] To facilitate understanding of this application, a more detailed description is provided below with reference to the accompanying drawings and specific embodiments. It should be noted that when an element is described as "fixed to" another element, it can be directly on the other element, or one or more intermediate elements may exist between them. When an element is described as "connected" to another element, it can be directly connected to the other element, or one or more intermediate elements may exist between them. The terms "upper," "lower," "inner," "outer," "vertical," "horizontal," etc., used in this specification indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.
[0019] Unless otherwise defined, all technical and scientific terms used in this specification have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the scope of the application. The term "and / or" as used in this specification includes any and all combinations of one or more of the associated listed items.
[0020] Furthermore, the technical features involved in the different embodiments of this application described below can be combined with each other as long as they do not conflict with each other.
[0021] Please see Figures 1 to 4 This application provides a propeller 100, including a propeller clamp assembly 31, an adjustment device 32, a drive device 20, and a blade body 10. The adjustment device 32 includes a first adjustment component 321, which is rotatably connected to one end of the propeller clamp assembly 31. The first adjustment component 301 includes a first pitch chamber 3210, a first pitch block 328, a first pitch shaft 323, and a first blade fixing member 40. The first pitch chamber 3210 has a first pitch chamber 3210 compartment, and the first pitch block 328 is detachably disposed in the first pitch chamber 3210 compartment. The first pitch block 328 has a plurality of first abutment portions 3281 with different preset angles. One end of the first pitch shaft 323 extends into the first pitch chamber 3210 compartment and abuts against one of the first abutment portions 3281, and the other end of the first pitch shaft 323 extends out of the first pitch chamber 3210 and is connected to the first blade fixing member 40. The adjusting device 32 is fixed to the driving device 20, and the blade body 10 is fixedly connected to the adjusting device 32.
[0022] In this embodiment, the first adjustment component 301 further includes an elastic rubber pad 3211 and a first fixing member 3212. A first tightening part 32105 is provided at the bottom of the first pitch chamber 3210, and the elastic rubber pad 3211 is fixed to the first tightening part 32105 by the first fixing member 3212. The elastic rubber pad 3211 is disposed between the first pitch chamber 3210 and the propeller clamp base 314. When the propeller 100 is working, the first blade 101 will vibrate during rotation, and this vibration is transmitted to the propeller clamp assembly 3131 through the adjustment component 32. The elastic rubber pad 3211 can absorb and buffer this vibration impact, reduce the direct force of the adjustment component 32 on the propeller clamp assembly 3131, thereby reducing the vibration and noise during the operation of the adjustment device 32, improving the operational stability of the propeller 100, and extending the service life of each component.
[0023] In this embodiment of the application, with the above structure, the user can change the pitch angle of the propeller blade by replacing the first contact part 3281 that abuts the first pitch block 328 and the first pitch shaft 323, thereby adapting to the needs of different altitude environments and flight scenarios. The overall structure is simple and compact, does not require the configuration of a servo drive mechanism, and is convenient to maintain and highly reliable.
[0024] Please refer to the following: Figures 3 to 6 This embodiment provides a detailed description of the specific structure of the first adjusting block 328.
[0025] The first pitch adjustment block 328 has a polyhedral structure, specifically a tetrahedral structure. The top surface of the first pitch adjustment block 328 has a through hole for the first fastener 326 to pass through, and each of the four sides has a first abutment portion 3281, each being an inclined groove. The inclination angle increments of the four inclined grooves are 0°, 2.50°, 5.00°, and 10.00°, respectively, corresponding to blade pitch angles of 11.6°, 14.1°, 16.6°, and 21.6°.
[0026] The first pitch adjustment chamber 3210 is also provided with a first outlet 32102 communicating with the first pitch adjustment chamber 32101, and the first pitch adjustment shaft 323 passes through the first outlet 32102. The first pitch adjustment shaft 323 is provided with a first abutment limiting platform 3231, which is located inside the first pitch adjustment chamber 32101. The first abutment limiting platform 3231 is embedded in an inclined groove and abuts against the first abutment part 3281. Through the groove-platform fitting of the inclined groove and the first abutment limiting platform 3231, compared with simple surface contact, this structure can provide a more stable fit relationship, effectively limit the radial displacement of the first pitch adjustment shaft 323, and ensure the accuracy and stability of pitch angle transmission.
[0027] The bottom of the first adjustment chamber 3210 is also provided with a first tightening part 32104. The first adjustment assembly also includes a first adjustment chamber cover plate 327 and a first fastener 326. The first adjustment chamber cover plate 327 covers the opening of the first adjustment chamber chamber 32101. The first fastener 326 passes through the through hole on the top surface of the first adjustment chamber cover plate 327 and the first adjustment block 328 in sequence and is fixed to the first tightening part 32104 on the first adjustment chamber 3210.
[0028] When adjusting the pitch, the user removes the first fastener 326 and the first pitch adjustment chamber cover 327, rotates the first pitch adjustment block 328 so that the inclined groove of the desired angle faces the first pitch adjustment shaft 323, so that the first abutment limiting platform 3231 is embedded in the corresponding inclined groove, and reinstalls it into the first pitch adjustment chamber 32101 and tightens it to complete the pitch angle adjustment.
[0029] In this embodiment, each first contact portion 3281 of the first adjusting block 328 adopts an inclined groove structure, which has the following technical advantages compared with the traditional inclined surface structure: First, the fit is more stable: the inclined groove and the first abutment limiting platform 3231 form a groove-platform fitting, and the contact area is larger than the point contact or line contact of the inclined surface, which can withstand a larger working load and maintain a stable fit relationship when the blade rotates at high speed and generates vibration.
[0030] Second, the positioning accuracy is higher: the inclined groove has a guiding and limiting function for the first abutting limiting stage 3231, which can ensure that the first abutting limiting stage 3231 is accurately embedded in the preset position and avoid pitch angle error caused by assembly deviation.
[0031] Third, it has stronger resistance to displacement: the groove wall of the inclined groove can effectively limit the radial displacement of the first adjusting shaft 323, prevent the first adjusting shaft 323 from shifting during operation, and ensure the long-term stability of the pitch angle.
[0032] Please continue to participate. Figures 4 to 10 Based on the above embodiments, this embodiment provides a detailed description of the specific structure of the first pitch adjustment shaft 323 and the first blade fixing member 40.
[0033] Please see Figure 8The first pitch control chamber 3210 is also provided with a first outlet 32102 communicating with the chamber 32101 of the first pitch control chamber 3210, and the first pitch control shaft 323 passes through the first outlet 32102. The first pitch control shaft 323 is provided with a first abutting limiting platform 3231, which is located inside the chamber 32101 of the first pitch control chamber 3210 and abuts against the first abutting part 3281. By abutting the first abutting limiting platform 3231 against the first abutting part 3281 on the first pitch control block 328 at different inclination angles, the first pitch control shaft 323 can receive the preset angle set by the first pitch control block 328, and then transmit the angle to the blade body 10.
[0034] Please see Figure 1 The blade body 10 includes a first blade 101, please refer to... Figures 9 to 11 The first blade fixing component 40 includes a first blade fixing upper plate 322, a first blade fixing lower plate 324, a first blade fixing component 40321, and a first blade fixing shaft 325. The first blade fixing upper plate 322 and the first blade fixing lower plate 324 are both sleeved on the first pitch adjusting shaft 323, and the first blade 101 is clamped between the first blade fixing upper plate 322 and the first blade fixing lower plate 324. The first blade fixing shaft 325 passes sequentially through the first blade fixing upper plate 322, the first blade 101, and the first blade fixing lower plate 324, and is fixedly connected by screws through the first blade fixing component 40321.
[0035] In this embodiment of the application, the first blade 101 is reliably clamped and fixed between the first blade fixing upper plate 322 and the first blade fixing lower plate 324 through the above structure. The through connection of the first blade fixing shaft 325 ensures the stability of the blade installation and facilitates the disassembly and replacement of the first blade 101.
[0036] Furthermore, the first blade fixing upper plate 322 is provided with a first upper plate anti-rotation groove 3221, and the first blade fixing lower plate 324 is provided with a first lower plate anti-rotation groove 3241. The first pitch shaft 323 is also provided with a first anti-rotation limiting platform 3232, which is engaged with the first upper plate anti-rotation groove 3221 and the first lower plate anti-rotation groove 3241 respectively. Through the engagement of the above structures, when the first blade 101 is subjected to aerodynamic forces during flight, it can effectively prevent the first blade fixing upper plate 322 and the first blade fixing lower plate 324 from circumferentially twisting relative to the first pitch shaft 323, ensuring the stability of the blade pitch angle.
[0037] The first blade fixing upper plate 322 is also provided with a first upper plate rotation groove 3222, and the first blade fixing lower plate 324 is also provided with a first lower plate rotation groove 3242. The first pitch shaft 323 is also provided with a first rotating ring 3233, which engages with both the first upper plate rotation groove 3222 and the first lower plate rotation groove 3242. Through the engagement of the rotation grooves and the rotating ring, the first blade fixing upper plate 322, the first blade fixing lower plate 324, and the first pitch shaft 323 form a single unit, enabling synchronous rotation of all three. When the first pitch shaft 323 abuts against different first contact portions 3281 of the first pitch block 328, resulting in different tilt angles, the first blade fixing upper plate 322 and the first blade fixing lower plate 324 can rotate synchronously, thereby driving the first blade 101 to achieve corresponding pitch angle changes.
[0038] In summary, the cooperation between the first anti-rotation limiting platform 3232 and the first upper plate anti-rotation groove 3221 and the first lower plate anti-rotation groove 3241 achieves the anti-torsion function, and the cooperation between the first rotating ring 3233 and the first upper plate rotating groove 3222 and the first lower plate rotating groove 3242 achieves the synchronous rotation function. The two sets of cooperative structures work together to ensure the reliability of the connection between the first blade fixing component 40 and the first pitch shaft 323 and the accuracy of angle transmission.
[0039] Please reconsider. Figure 4 Based on the above embodiments, this embodiment provides a detailed description of the specific structure of the propeller clamp assembly 3131.
[0040] The propeller clamp assembly 3131 includes a propeller clamp base 314, a propeller clamp top cover 312, a rotating shaft 315, and a first rotating shaft fastener 311. The rotating shaft 315 is disposed on the propeller clamp base 314, and the first pitch adjustment chamber 3210 is rotatably sleeved on one end of the rotating shaft 315. The propeller clamp top cover 312 is disposed on the propeller clamp base 314, and the first rotating shaft fastener 311 passes through the propeller clamp top cover 312 and the propeller clamp base 314 in sequence before being fixedly connected to the rotating shaft 315. With the above structure, the first adjustment component 30132 can rotate relative to the propeller clamp assembly 3131 around the rotating shaft 315, thereby realizing the folding and storage function of the propeller body, which facilitates the transportation and storage of the UAV.
[0041] Furthermore, the propeller clamp assembly 3131 also includes a wear-resistant washer 313 and a wear-resistant bushing 329. One end of the first pitch adjustment chamber 3210 is provided with a first pitch adjustment chamber 3210 rotation groove 32103, and the wear-resistant bushing 329 is embedded in the first pitch adjustment chamber 3210 rotation groove 32103. The first pitch adjustment chamber 3210 is rotatably mounted on the rotating shaft 315 via the wear-resistant bushing 329. The wear-resistant washer 313 is disposed between the first pitch adjustment chamber 3210 and the propeller clamp base 314. In this embodiment, the wear-resistant bushing 329 creates a wear-resistant rotational fit between the first pitch adjustment chamber 3210 and the rotating shaft 315, reducing wear caused by direct contact and extending service life. The wear-resistant washer 313 reduces the frictional resistance between the first pitch adjustment chamber 3210 and the propeller clamp base 314, making the first adjustment assembly 30132 rotate more smoothly during folding and unfolding.
[0042] In this embodiment, the propeller clamp assembly 3131 further includes a propeller clamp fixing member 21, which is disposed on the propeller clamp base 314. The propeller clamp assembly 3131 is fixed to the drive device 20 by the propeller clamp fixing member 21. The drive device 20 may be a motor, and the motor output shaft is connected to the propeller clamp fixing member 21. The rotation of the motor output shaft drives the entire propeller 100 to rotate, generating lift.
[0043] The propeller clamp fixing component 21 enables a reliable fixed connection between the propeller clamp assembly 3131 and the drive device 20, ensuring that the torque output by the drive device 20 can be effectively transmitted to the propeller body 10, while facilitating the disassembly and replacement of the propeller body 10.
[0044] Please see Figure 1 and Figure 2 Based on the above embodiments, this embodiment provides a detailed description of the structure of the second adjustment component 302 and the second blade 102.
[0045] The adjustment device 32 also includes a second adjustment component 302, which is rotatably connected to the other end of the propeller clamp assembly 3131 and is located on both sides of the propeller clamp assembly 3131, forming a symmetrical arrangement. The propeller body 10 also includes a second propeller blade 102.
[0046] The second adjustment assembly 302 includes a second pitch chamber, a second pitch block, a second pitch shaft, and a second blade fixing member. The second pitch chamber has a second pitch chamber compartment. The second pitch block is detachably disposed within the second pitch chamber compartment and has multiple second abutment portions with different preset angles. One end of the second pitch shaft extends into the second pitch chamber compartment and abuts against one of the second abutment portions. The other end of the second pitch shaft extends out of the second pitch chamber and connects to the second blade fixing member. The second blade 102 is fixedly connected to the second blade fixing member.
[0047] The structure of the second adjustment component 302 corresponds to that of the first adjustment component 301, and the two work together to form a complete dual-bladed propeller 100 structure. It should be noted that, depending on the rotation direction of the propeller 100, the first blade 101 is a CCW (counter-clockwise) blade, and the second blade is a CW (clockwise) blade. Correspondingly, the tilt angles of the contact portions on the first and second adjustment blocks are set in opposite directions. Specifically, if the tilt angle of one side of the first adjustment block 328 is positive, the tilt angle of the corresponding side of the second adjustment block is negative, ensuring that when the two blades are used together on the same UAV, they can generate lift and torque in the correct direction.
[0048] By combining the first adjustment component 301 and the second adjustment component 302, the user can independently adjust the pitch angle of the two propeller blades to meet the needs of different flight conditions.
[0049] In this embodiment, the first pitch control chamber 3210 can rotate around the pivot 315 between an extended position and a folded position. When the first pitch control chamber 3210 is in the extended position, the extension direction of the first blade 101 is perpendicular to the axial direction of the pivot 315, and the propeller 100 is in working condition and can rotate normally to generate lift. When the first pitch control chamber 3210 is in the folded position, the extension direction of the first blade 101 is parallel to the axial direction of the pivot 315, and the first blade 101 retracts along the fuselage direction, and the propeller 100 is in a retracted state.
[0050] Similarly, the second adjustment component 302 can also rotate around the pivot 315 between the unfolded position and the folded position. When both the first adjustment component 301 and the second adjustment component 302 are in the folded position, the first blade 101 and the second blade 102 are retracted along the fuselage direction, and the unfolded size of the entire propeller 100 is greatly reduced, which facilitates the transportation, storage and carrying of the UAV.
[0051] The wear-resistant bushing 329 and wear-resistant washer 313 ensure the smooth rotation of the first adjustment component 301 and the second adjustment component 302 during unfolding and folding, reducing wear on the components caused by repeated folding operations.
[0052] In this embodiment, the first blade 101 is a counter-clockwise (CCW) blade, and the second blade 102 is a clockwise (CW) blade. Correspondingly, the tilting direction of each first abutment portion 3281 on the first pitch block 328 is opposite to the tilting direction of each second abutment portion on the second pitch block.
[0053] Specifically, such as Figure 11As shown, the four sides of the first pitch control block 328 are provided with tilting grooves with tilt angle increments of 0°, 2.50°, 5.00°, and 10.00°, respectively, corresponding to blade pitch angles of 11.6°, 14.1°, 16.6°, and 21.6°. The second pitch control block also has tilting grooves with the same angle increments on its four sides, but the tilting direction is opposite to that of the first pitch control block 328.
[0054] With the aforementioned reverse configuration, when the first blade 101 and the second blade 102 are mounted on opposite sides of the same drone, the blades on both sides can generate lift in the same direction as they rotate in opposite directions, while simultaneously canceling out the anti-torque, ensuring the stability of the drone's flight attitude. When adjusting the pitch, the user needs to simultaneously adjust the pitch adjustment blocks on both sides to the corresponding tilt slots to maintain the consistency of the pitch angle of the blades on both sides.
[0055] Furthermore, the second pitch block has a polyhedral structure, specifically a tetrahedral structure, corresponding to the structure of the first pitch block 328. Multiple second abutment portions are respectively disposed on different sides of the second pitch block, each abutment portion being an inclined groove. The four sides of the second pitch block are respectively provided with inclined grooves of different inclination angles. The inclination angle increments of the four inclined grooves are the same as those of the first pitch block 328, namely 0°, 2.50°, 5.00°, and 10.00°, but the inclination directions are opposite to those of the first pitch block 328, to accommodate the clockwise rotation of the second blade 102.
[0056] The second adjusting assembly 302 also includes a second adjusting chamber cover and a second fastener. The second adjusting chamber cover covers the opening of the second adjusting chamber, and the second fastener passes through the second adjusting chamber cover and the second adjusting block in sequence and is fixed to the second screw portion on the second adjusting chamber. With the above structure, the second adjusting block is detachably fixed in the second adjusting chamber, which facilitates the user to adjust the pitch angle.
[0057] The second pitch control chamber is also provided with a second outlet that communicates with the second pitch control chamber chamber, and the second pitch control shaft passes through the second outlet. The second pitch control shaft is provided with a second abutment limiting platform, which is located inside the second pitch control chamber chamber and abuts against the second abutment part. By abutting against the second abutment part on the second pitch control block at different inclination angles with the second abutment limiting platform, the second pitch control shaft can receive the preset angle set by the second pitch control block, and then transmit the angle to the second blade 102.
[0058] The second blade fixing component includes a second blade fixing upper plate, a second blade fixing lower plate, and a second blade fixing shaft. Both the second blade fixing upper plate and the second blade fixing lower plate are sleeved on the second pitch shaft, and the second blade 102 is clamped between the second blade fixing upper plate and the second blade fixing lower plate. The second blade fixing shaft passes sequentially through the second blade fixing upper plate, the second blade 102, and the second blade fixing lower plate, and is fixedly connected by fasteners. Through this structure, the second blade 102 is reliably clamped and fixed between the second blade fixing upper plate and the second blade fixing lower plate.
[0059] In this embodiment, the upper plate of the second blade fixing is provided with a second upper plate anti-rotation groove, and the lower plate of the second blade fixing is provided with a second lower plate anti-rotation groove. A second anti-rotation limiting platform is also provided on the second pitch shaft, and the second anti-rotation limiting platform engages with the second upper plate anti-rotation groove and the second lower plate anti-rotation groove, respectively. Through the engagement of the anti-rotation grooves and the anti-rotation limiting platforms, when the second blade 102 is subjected to aerodynamic forces during flight, the circumferential torsion of the upper and lower plates of the second blade fixing relative to the second pitch shaft can be effectively prevented, ensuring the stability of the pitch angle of the second blade 102.
[0060] The second blade fixing upper plate is also provided with a second upper plate rotation groove, and the second blade fixing lower plate is also provided with a second lower plate rotation groove. The second pitch shaft is also provided with a second rotating ring, which engages with both the second upper plate rotation groove and the second lower plate rotation groove. Through the engagement of the rotation grooves and the rotating ring, the second blade fixing upper plate, the second blade fixing lower plate, and the second pitch shaft form a single unit, enabling synchronous rotation of all three. When the second pitch shaft abuts against different second contact parts of the second pitch block, resulting in different tilt angles, the second blade fixing upper plate and the second blade fixing lower plate can rotate synchronously, thereby driving the second blade 102 to achieve corresponding pitch angle changes.
[0061] In summary, the cooperation between the second anti-rotation limiting platform and the anti-rotation groove achieves the anti-torsion function, and the cooperation between the second rotating ring and the rotating groove achieves the synchronous rotation function. The two sets of cooperative structures work together to ensure the reliability of the connection between the second blade fixing component and the second pitch shaft, as well as the accuracy of angle transmission.
[0062] In this embodiment, the propeller clamp assembly 31 further includes a second wear-resistant washer and a second wear-resistant bushing. One end of the second pitch chamber has a second pitch chamber rotation groove, and the second wear-resistant bushing is embedded in the second pitch chamber rotation groove. The second pitch chamber is rotatably fitted onto the other end of the rotating shaft via the second wear-resistant bushing. The second wear-resistant washer is disposed between the second pitch chamber and the propeller clamp base 314. The second wear-resistant bushing creates a wear-resistant rotational fit between the second pitch chamber and the rotating shaft, reducing wear caused by direct contact and extending service life. The second wear-resistant washer reduces the frictional resistance between the second pitch chamber and the propeller clamp base 314, making the second adjustment assembly 302 rotate more smoothly during folding and unfolding.
[0063] The second adjustment assembly 302 also includes a second elastic rubber pad and a fourth fastener. A second adjustment chamber screw-in portion is provided on the second adjustment chamber, and the second elastic rubber pad is fixed to the second adjustment chamber screw-in portion by the fourth fastener. The second elastic rubber pad is disposed between the second adjustment chamber and the propeller clamp base 314. When the propeller 100 is operating, the second blade 102 will vibrate during rotation, and this vibration is transmitted to the propeller clamp assembly 31 through the second adjustment assembly 302. The second elastic rubber pad can absorb and buffer this vibration impact, reducing the direct force of the second adjustment assembly 302 on the propeller clamp assembly 31, thereby reducing vibration and noise during device operation and improving the operational stability of the propeller 100. This application provides a propeller 100, in which a first pitch block 328 is detachably installed in the first pitch control chamber 3210, and the first pitch block 328 has multiple first abutment portions 3281 with different preset angles. A first pitch control shaft 323 abuts against one of the first abutment portions 3281. The user can change the pitch angle of the propeller blade by changing the abutment portion between the first pitch block 328 and the first pitch control shaft 323, thereby adapting to the needs of different altitude environments and flight scenarios. Compared with electric variable pitch systems, the propeller 100 in this application does not require a servo drive mechanism, has a simple and compact overall structure, is small in size and light in weight, and has no risk of electrical component failure, making maintenance convenient and highly reliable. Compared with fixed pitch propeller blades, this application allows manual adjustment of the propeller blade pitch according to actual usage needs. When the UAV operates in plateau or high-altitude areas, a larger pitch angle can be selected to obtain sufficient lift without compensating by increasing the motor speed, reducing the performance requirements of the drive system and improving flight efficiency and endurance.
[0064] This application also provides a drone, including the propeller 100 described in any of the above embodiments.
[0065] A drone typically includes a fuselage, a power system, a flight control system, and a propeller 100. The drone in this embodiment uses the aforementioned propeller 100, which is fixed to the drive device 20 by a propeller clamp 21. The drive device 20 can be a motor, and the motor output shaft drives the propeller 100 to rotate and generate lift.
[0066] Because the propeller 100 of this application has a manually adjustable pitch function, the drone equipped with this propeller 100 can adapt to the needs of different altitude environments and flight scenarios. When the drone needs to perform low-load cruise operations in low-altitude areas, the user can adjust the pitch angle to a smaller angle to obtain lower energy consumption and longer endurance. When the drone needs to operate in plateau or high-altitude areas, or needs to perform tasks such as heavy-load takeoff and rapid climb, the user can adjust the pitch angle to a larger angle to obtain sufficient lift and thrust. There is no need to increase the motor speed to compensate for the insufficient lift caused by the decrease in air density, which reduces the requirements for the performance of the drive system and improves the drone's operational capability and flight efficiency in complex environments.
[0067] Meanwhile, since the propeller 100 of this application adopts a mechanical manual pitch adjustment structure, compared with the electric pitch adjustment system, there is no need to configure a servo drive mechanism and related electrical control system. The overall structure is simple and compact, lightweight, highly reliable, and easy to maintain, which can effectively reduce the manufacturing cost and operating cost of the UAV.
[0068] The above description is merely an embodiment of this application and does not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.
Claims
1. A propeller, characterized in that, include: propeller clamp assembly; An adjustment device, the adjustment device including a first adjustment component, the first adjustment component being rotatably connected to one end of the paddle clamp assembly; The first adjustment assembly includes a first pitch chamber, a first pitch block, a first pitch shaft, and a first blade fixing component. The first pitch control chamber is provided with a first pitch control chamber compartment. The first pitch control block is detachably disposed in the first pitch control chamber compartment. The first pitch control block is provided with a plurality of first abutting parts with different preset angles. One end of the first pitch control shaft extends into the first pitch control chamber compartment and abuts against one of the first abutting parts. The other end of the first pitch control shaft passes through the first pitch control chamber and is connected to the first blade fixing member. A driving device, wherein the adjusting device is fixed to the driving device; The blade body is fixedly connected to the adjustment device.
2. The propeller according to claim 1, characterized in that, The first adjusting block has a polyhedral structure, with multiple first abutting portions respectively disposed on different sides of the first adjusting block, and each first abutting portion being an inclined groove. The first adjustment assembly further includes a first adjustment chamber cover and a first fastener. The first adjustment chamber cover is disposed over the opening of the first adjustment chamber compartment, and the first fastener passes through the first adjustment chamber cover and the first adjustment block in sequence and is fixed to the first adjustment chamber.
3. The propeller according to claim 1, characterized in that, The first adjustable gap chamber is also provided with a first outlet hole communicating with the chamber of the first adjustable gap chamber, and the first adjustable gap shaft passes through the first outlet hole. The first adjusting shaft is provided with a first abutting limiting platform, which is located in the first adjusting compartment and embedded in the inclined groove to abut against the first abutting part.
4. The propeller according to claim 3, characterized in that, The blade body includes a first blade. The first blade fixing component includes a first blade fixing upper plate, a first blade fixing lower plate, and a first blade fixing shaft. The first blade fixing upper plate and the first blade fixing lower plate are both sleeved on the first pitch shaft. The first blade is sandwiched between the first blade fixing upper plate and the first blade fixing lower plate. The first blade fixing shaft passes through the first blade fixing upper plate, the first blade and the first blade fixing lower plate in sequence and is fixedly connected.
5. The propeller according to claim 4, characterized in that, The first blade fixing upper plate is provided with a first upper plate anti-rotation groove, the first blade fixing lower plate is provided with a first lower plate anti-rotation groove, and the first pitch shaft is also provided with a first anti-rotation limiting platform. The first anti-rotation limiting platform is respectively engaged with the first upper plate anti-rotation groove and the first lower plate anti-rotation groove.
6. The propeller according to claim 5, characterized in that, The first blade fixing upper plate is also provided with a first upper plate rotation groove, and the first blade fixing lower plate is also provided with a first lower plate rotation groove. The first adjusting shaft is also provided with a first rotating ring, which is respectively engaged with the rotating groove of the first upper plate and the rotating groove of the first lower plate.
7. The propeller according to claim 6, characterized in that, The propeller clamp assembly includes a propeller clamp base, a propeller clamp top cover, a first rotating shaft, and a first rotating shaft fastener. The propeller clamp base is sleeved on the first rotating shaft, the first pitch adjustment chamber is rotatably sleeved on one end of the first rotating shaft, the propeller clamp cover is placed on the propeller clamp base, and the first rotating shaft fastener passes through the propeller clamp cover and the propeller clamp base in sequence and is fixedly connected to the first rotating shaft.
8. The propeller according to claim 7, characterized in that, The propeller clamp assembly also includes wear-resistant washers and wear-resistant bushings. One end of the first pitch chamber is provided with a first pitch chamber rotation groove, the wear-resistant bushing is embedded in the first pitch chamber rotation groove, the first pitch chamber is rotatably sleeved on the first rotating shaft through the wear-resistant bushing, and the wear-resistant washer is disposed between the first pitch chamber and the propeller clamp base.
9. The propeller according to claim 1, characterized in that, The adjusting device further includes a second adjusting component, which is rotatably connected to the other end of the propeller clamp assembly. The propeller body also includes a second propeller blade. The second adjustment assembly includes a second pitch chamber, a second pitch block, a second pitch shaft, and a second blade fixing member. The second pitch chamber has a second pitch chamber compartment. The second pitch block is detachably disposed in the second pitch chamber compartment. The second pitch block has multiple second abutment portions with different preset angles. One end of the second pitch shaft extends into the second pitch chamber compartment and abuts against one of the second abutment portions. The other end of the second pitch shaft passes through the second pitch chamber and is connected to the second blade fixing member. The second blade is fixedly connected to the second blade fixing member.
10. A drone, characterized in that, Including the propeller as described in any one of claims 1-9.