Blades, propellers, powertrains and drones
By optimizing the pitch angle distribution of the main blade section, the problems of poor overall propeller efficiency and noise reduction were solved, achieving the effects of reducing noise and improving efficiency.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- MEITUAN TECH CO LTD
- Filing Date
- 2025-05-19
- Publication Date
- 2026-05-26
AI Technical Summary
In existing technologies, propellers have low overall efficiency and poor noise reduction.
The design reduces the pitch angle of the main blade section from a positive value to a negative value, optimizes the angle of attack distribution at different radial positions of the blade, and sets the pitch angle near the blade root section to a positive value and the pitch angle far from the blade root section to a negative value, in order to balance lift and drag, suppress tip turbine, and reduce airflow separation noise.
It effectively reduces noise, improves overall efficiency, and enhances reliability and stability.
Smart Images
Figure CN224277606U_ABST
Abstract
Description
Technical Field
[0001] This disclosure relates to the field of aircraft technology, specifically to a blade, propeller, powertrain, and unmanned aerial vehicle (UAV). Background Technology
[0002] As an important component of drones, propellers are usually connected to motors through a hub to provide thrust or lift for the drone.
[0003] Among related technologies, propellers have relatively low overall efficiency and poor noise reduction effect. Utility Model Content
[0004] The purpose of this disclosure is to provide a blade, propeller, powertrain, and drone that can effectively reduce noise, thereby at least partially solving the aforementioned technical problems.
[0005] To achieve the above objectives, a first aspect of this disclosure provides a blade comprising a root section and a main body section arranged radially in sequence, wherein the pitch angle of the main body section decreases from a positive value to a negative value in a radial direction and in a direction away from the root section.
[0006] Optionally, the main body section includes a middle section and a blade tip section, the blade root section, the middle section and the blade tip section are connected in sequence, and at least part of the blade tip section has a negative blade pitch angle.
[0007] Optionally, the propeller tip section includes a swept portion, and at least a portion of the swept portion has a negative pitch angle.
[0008] Optionally, the leading edge of the blade includes a first leading edge segment located in the swept portion, and the trailing edge of the blade includes a first trailing edge segment located in the swept portion, both the first leading edge segment and the first trailing edge segment extending in an arc.
[0009] Optionally, the pitch angle of the blade is in the range of 19.88° to -0.17°.
[0010] Optionally, the chord length of the main body segment decreases radially and in a direction away from the paddle root segment.
[0011] Optionally, the chord length of the blade is in the range of 15mm to 60mm.
[0012] A second aspect of this disclosure provides a propeller including a hub and the aforementioned blades connected together.
[0013] A third aspect of this disclosure provides a powertrain including an electric motor and the aforementioned propeller, the propeller blades being connected to the electric motor via a hub.
[0014] A fourth aspect of this disclosure provides an unmanned aerial vehicle (UAV) including the aforementioned powertrain.
[0015] Through the above technical solution, the pitch angle of the main body section is reduced from a positive value to a negative value to optimize the angle of attack distribution at different radial positions of the blade, balancing lift and drag. The pitch angle of the main body section near the blade root is positive, providing high lift, while the pitch angle of the main body section away from the blade root is negative, which can suppress tip turbines, reduce noise caused by airflow separation, and reduce induced drag at the blade tip, thereby improving overall efficiency. Therefore, the blade provided in this disclosure can effectively reduce noise, improve overall efficiency, and has greater reliability and stability in use.
[0016] Other features and advantages of this disclosure will be described in detail in the following detailed description section. Attached Figure Description
[0017] The accompanying drawings are provided to further illustrate the present disclosure and form part of the specification. They are used together with the following detailed description to explain the present disclosure, but do not constitute a limitation thereof. In the drawings:
[0018] Figure 1 This is a schematic diagram of the overall structure of the powertrain provided in the exemplary embodiments of this disclosure;
[0019] Figure 2 This is a top view of the blades provided in the exemplary embodiments of this disclosure. Figure 1 ;
[0020] Figure 3 This is a top view of the blades provided in the exemplary embodiments of this disclosure. Figure 2 ;
[0021] Figure 4 This is a left view of the blade provided in an exemplary embodiment of this disclosure;
[0022] Figure 5 This is a top view of the blades provided in the exemplary embodiments of this disclosure. Figure 3 ;
[0023] Figure 6 yes Figure 5 A cross-sectional view of the DD position in the middle;
[0024] Figure 7 yes Figure 5 A cross-sectional view of the EE location;
[0025] Figure 8 yes Figure 5 A cross-sectional view at position FF;
[0026] Figure 9 yes Figure 5 A cross-sectional view of the GG location;
[0027] Figure 10 yes Figure 5 A cross-sectional view at the HH position;
[0028] Figure 11 yes Figure 5 A sectional view at position II;
[0029] Figure 12 yes Figure 5 A cross-sectional view of the middle JJ position;
[0030] Figure 13 yes Figure 5 A cross-sectional view at position KK;
[0031] Figure 14 yes Figure 5 A sectional view at the LL position;
[0032] Figure 15 yes Figure 5 A cross-sectional view at the MM position.
[0033] Explanation of reference numerals in the attached figures
[0034] 1. Blade; 10. Root section; 11. Main body section; 110. Middle section; 111. Tip section; 1110. Sweep section; 12. First leading edge section; 13. First trailing edge section;
[0035] 2. Propeller hub; 3. Motor. Detailed Implementation
[0036] The specific embodiments of this disclosure will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.
[0037] In this disclosure, unless otherwise stated, the terms “first” and “second” are used to distinguish one element from another and are not sequential or important. In addition, when the following description refers to the accompanying drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements.
[0038] according to Figures 1 to 15 As shown, in a first aspect of this disclosure, a propeller 1 is provided for providing lift for the flight of a drone. The propeller 1 may include a root section 10 and a main body section 11 arranged radially in sequence. The pitch angle of the main body section 11 decreases from a positive value to a negative value in the radial direction and in a direction away from the root section 10.
[0039] Through the above technical solution, the pitch angle of the main body section 11 is reduced from a positive value to a negative value to optimize the angle of attack distribution of the blade 1 at different radial positions, balance lift and drag. The pitch angle of the main body section 11 near the blade root section 10 is positive, which can provide high lift. The pitch angle of the main body section 11 far from the blade root section 10 is negative, which can suppress the tip turbine, reduce noise caused by airflow separation, and at the same time reduce induced drag at the tip, thereby improving overall efficiency.
[0040] It should be noted that the positive and negative values mentioned above only represent the direction of the blade 1 chord length relative to the plane of rotation. For example, when the pitch angle is positive, the blade 1 chord length is inclined upward toward the plane of rotation, and when the pitch angle is negative, the blade 1 chord length is inclined downward toward the plane of rotation.
[0041] The plane of rotation can be a plane perpendicular to the pivot axis of the hub 2, and the pitch angle refers to the angle between the chord line of the blade 1 and the plane of rotation. The definition of the pitch angle is well known to those skilled in the art, and will not be repeated here.
[0042] In addition, the blade 1 provided in this disclosure is applicable to drones or other aircraft with a fixed pitch angle (or fixed pitch propeller).
[0043] Optionally, the pitch angle of the main body section 11 can be between 19.88° and -0.17°. For example, the position with the largest pitch angle in the main body section 11 can be used as the boundary between the main body section 11 and the root section 10; the chord length of the blade 1 can be between 15mm and 60mm. This disclosure does not specifically limit this.
[0044] In some feasible ways, for example, refer to Figures 2 to 4 As shown, the chord length of the main body section 11 can decrease in the radial direction and away from the blade root section 10 to optimize lift distribution and reduce overall weight.
[0045] In some feasible ways, for example, refer to Figure 2 and Figure 3 As shown, the main body section 11 may include a middle section 110 and a tip section 111. The root section 10, the middle section 110, and the tip section 111 are connected in sequence. At least part of the tip section 111 has a negative pitch angle to suppress the turbine strength of the tip section 111, reduce noise, and reduce energy loss. Through the synergistic effect of the middle section 110 and the tip section 111, the aerodynamic requirements at different speeds can be met.
[0046] In some feasible ways, for example, refer to Figures 2 to 4As shown, the blade tip section 111 may include a swept portion 1110, at least a portion of which has a negative pitch angle. By designing the pitch angle of the swept portion 1110 to be negative, the drag at the blade tip 1 can be reduced, airflow control optimized, and stability improved at high speeds.
[0047] In some feasible ways, for example, refer to Figures 2 to 4 As shown, the leading edge of the blade 1 may include a first leading edge segment 12 located in the swept portion 1110, and the trailing edge of the blade 1 may include a first trailing edge segment 13 located in the swept portion 1110. Both the first leading edge segment 12 and the first trailing edge segment 13 extend in an arc. The arc design can optimize airflow adhesion and pressure distribution, effectively reduce turbulence, avoid stress concentration, and extend service life.
[0048] A second aspect of this disclosure provides a propeller comprising a hub 2 and blades 1 connected together, the blades 1 having all the beneficial effects of the above-described embodiments, which will not be repeated here.
[0049] A third aspect of this disclosure provides a powertrain including a motor 3 and a propeller, wherein the propeller blade 1 is connected to the motor 3 via a hub 2, and the propeller has all the beneficial effects described in the above-described embodiments, which will not be repeated here.
[0050] A fourth aspect of this disclosure provides an unmanned aerial vehicle (UAV) including a powertrain that has all the beneficial effects of the above-described embodiments, which will not be repeated here.
[0051] The parameters of the overall design of blade 1 are described below in a discretized manner. For details, please refer to [link / reference]. Figures 5 to 15 :
[0052] At a distance of 20% of the radial length of blade 1 from the center of hub 2 ( Figure 5 (At the DD position), the pitch angle a1 of blade 1 can be 19.88°, and the chord length L1 of blade 1 can be 60mm.
[0053] At a distance of 27% of the radial length of blade 1 from the center of hub 2 ( Figure 5 (At the EE position), the pitch angle α2 of blade 1 can be 21.30°, and the chord length L2 of blade 1 can be 56mm.
[0054] At a distance of 38% of the radial length of blade 1 from the center of hub 2 ( Figure 5 (At the FF position), the pitch angle α3 of blade 1 can be 18.84°, and the chord length L3 of blade 1 can be 50mm.
[0055] At a distance of 51% of the radial length of blade 1 from the center of hub 2 ( Figure 5(At the GG position), the pitch angle a4 of blade 1 can be 13.97°, and the chord length L4 of blade 1 can be 43mm.
[0056] At a distance of 63% of the radial length of blade 1 from the center of hub 2 ( Figure 5 (At the HH position), the pitch angle a5 of blade 1 can be 10.42°, and the chord length L5 of blade 1 can be 36mm.
[0057] At a distance of 74% of the radial length of blade 1 from the center of hub 2 ( Figure 5 (In the middle II position), the pitch angle α6 of blade 1 can be 8.76°, and the chord length L6 of blade 1 can be 30mm.
[0058] At a distance of 83% of the radial length of blade 1 from the center of hub 2 ( Figure 5 (At the middle JJ position), the pitch angle a7 of blade 1 can be 7.62°, and the chord length L7 of blade 1 can be 24mm.
[0059] At a distance of 91% of the radial length of blade 1 from the center of hub 2 ( Figure 5 (At the KK position), the pitch angle a8 of blade 1 can be 5.67°, and the chord length L8 of blade 1 can be 20mm.
[0060] At a distance of 96% of the radial length of blade 1 from the center of hub 2 ( Figure 5 (At the LL position), the pitch angle α9 of blade 1 can be 2.92°, and the chord length L9 of blade 1 can be 17mm.
[0061] At a distance of 100% of the radial length of blade 1 from the center of hub 2 ( Figure 5 (Middle MM position), blade 1 pitch angle α 10 The angle can be -0.17°, and the chord length L10 of blade 1 can be 15mm.
[0062] The other parts of the blade 1 not mentioned above can be obtained by fitting the specific parameter values mentioned above. This disclosure will not elaborate further here.
[0063] In the above embodiments, by discretization design, the range of the pitch angle and chord length of blade 1 is determined, avoiding excessive positive pitch angle that leads to increased drag and excessive negative pitch angle that leads to excessive reverse thrust. This can meet the needs under different speed conditions, improve overall efficiency, and effectively reduce noise.
[0064] The preferred embodiments of this disclosure have been described in detail above with reference to the accompanying drawings. However, this disclosure is not limited to the specific details of the above embodiments. Within the scope of the technical concept of this disclosure, various simple modifications can be made to the technical solutions of this disclosure, and these simple modifications all fall within the protection scope of this disclosure.
[0065] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable manner without contradiction. In order to avoid unnecessary repetition, this disclosure will not describe the various possible combinations separately.
[0066] Furthermore, various different embodiments of this disclosure can be combined in any way, as long as they do not violate the spirit of this disclosure, they should also be regarded as the content disclosed in this disclosure.
Claims
1. A blade, characterized in that, It includes a blade root section and a main body section arranged radially in sequence, and the blade pitch angle of the main body section decreases from a positive value to a negative value in a radial direction and in a direction away from the blade root section.
2. The blade according to claim 1, characterized in that, The main body section includes a middle section and a blade tip section. The blade root section, the middle section and the blade tip section are connected in sequence, and at least part of the blade tip section has a negative blade pitch angle.
3. The blade according to claim 2, characterized in that, The propeller tip section includes a swept portion, and at least a portion of the swept portion has a negative pitch angle.
4. The blade according to claim 3, characterized in that, The leading edge of the blade includes a first leading edge segment located in the swept portion, and the trailing edge of the blade includes a first trailing edge segment located in the swept portion. Both the first leading edge segment and the first trailing edge segment extend in an arc.
5. The blade according to claim 1, characterized in that, The pitch angle of the main body section ranges from 19.88° to -0.17°.
6. The blade according to claim 1, characterized in that, The chord length of the main body segment decreases radially and in a direction away from the paddle root segment.
7. The blade according to claim 1, characterized in that, The chord length of the blades ranges from 15mm to 60mm.
8. A propeller, characterized in that, It includes a connected hub and blades, wherein the blades are the blades described in any one of claims 1-7.
9. A powertrain, characterized in that, It includes an electric motor and the propeller of claim 8, wherein the propeller blades are connected to the electric motor via the propeller hub.
10. A drone, characterized in that, Includes the powertrain as described in claim 9.