Multi-rotor aircraft propeller suitable for plateau area

Abstract

The utility model relates to the technical field of multi-rotor aircrafts, and particularly discloses a multi-rotor aircraft propeller suitable for plateau areas, the spanwise direction is the direction from the blade root to the blade tip, the chordwise direction is the direction perpendicular to the spanwise direction, the distance between the front edge and the rear edge of the position where an airfoil is located is the chord length C of the airfoil, and the chord length C of the airfoil is larger than the chord length C of the airfoil. The included angle between the chord line of the airfoil and the blade rotor plane is a torsion angle alpha, the vertical connecting line between the rotation center of the propeller and the blade tip is L, the distance between the front edge point of the airfoil and the L is Yq, the distance between the rotation center of the propeller and the blade tip is R, and C, Yq and alpha are all maximum values at the position 35% R away from the blade root. C, alpha and Yq are gradually increased from the blade root to the maximum chord length position, and C, alpha and Yq are gradually reduced from the maximum chord length position to the blade tip. By adopting the structural design, the flight requirements of plateau areas can be met.

Description

Technical Field

[0001] The utility model relates to the technical field of multi-rotor aircraft, in particular to a multi-rotor aircraft propeller suitable for plateau areas. Background Art

[0002] A multi-rotor drone is a special type of unmanned helicopter with three or more rotor shafts. Currently, the propeller blades of multi-rotor drones are mainly designed for use in plain areas. When multi-rotor drones are used in plateaus, their aerodynamic performance is poor, lift is reduced, and such drones cannot fly. The reason is that the harsh environment and thin air in plateaus result in a very small air intake for drones, making it difficult for drones to generate thrust, and the driving force becomes weaker and difficult to drive the propellers. In addition, the higher the altitude, the thinner the air content, which also reduces the pulling force that the propeller blades can provide at the same speed, making it impossible for drones to achieve good maneuverability.

[0003] Therefore, the design of plateau propellers must be able to provide greater thrust at the same speed as the motor, so as to meet the use needs in plateau areas. However, due to the poor high-speed performance of the propeller, the aerodynamic efficiency drops rapidly when the flight speed deviates from the design point. Multi-rotor drones with propellers as the propulsion system are difficult to meet the design requirements of rapid climb and rapid maneuvering. Utility Model Content

[0004] The purpose of the utility model is to provide a multi-rotor aircraft propeller suitable for plateau areas to meet the flight requirements of climbing and rapid maneuvering in plateau areas.

[0005] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0006] The utility model provides a propeller for a multi-rotor aircraft suitable for plateau areas. The multi-rotor aircraft includes a rotating shaft, and blades of the propeller are fixedly connected to the rotating shaft. The span direction is the direction from the blade root to the blade tip, the chord direction is the direction perpendicular to the span direction, the airfoil is the inner profile of the cross section of the blade at any position in the span direction, the distance between the leading edge and the trailing edge at the position of the airfoil is the chord length C of the airfoil, the angle between the chord line of the airfoil and the blade rotor plane is the torsion angle alpha, the vertical line between the rotation center of the propeller and the blade tip is L, the distance between the leading edge point of the airfoil and L is Yq, the distance between the rotation center of the propeller and the blade tip is R, and at a position 35% R from the blade root, C, Yq and alpha are all maximum values, and C, alpha and Yq gradually increase from the blade root to the maximum chord length position, and gradually decrease from the maximum chord length position to the blade tip.

[0007] As an optimal technical solution for the above-mentioned multi-rotor aircraft propeller suitable for plateau areas, the cross-section where the airfoil is located is called the airfoil section, and the distance between the airfoil section and the rotation center is r, wherein, at r / R=20%, alpha, Yq / R and C / R satisfy: alpha=6.3°, Yq / R=0.053, C / R=0.1348.

[0008] As an optimal technical solution for the above-mentioned multi-rotor aircraft propeller suitable for plateau areas, at r / R=25%, alpha, Yq / R and C / R satisfy: alpha=12.599°, Yq / R=0.060952, C / R=0.1667.

[0009] As an optimal technical solution for the above-mentioned multi-rotor aircraft propeller suitable for plateau areas, at r / R=30%, alpha, Yq / R and C / R satisfy: alpha=18.479°, Yq / R=0.065143, C / R=0.1839.

[0010] As an optimal technical solution for the above-mentioned multi-rotor aircraft propeller suitable for plateau areas, at r / R=35%, alpha, Yq / R and C / R satisfy: alpha=20.998°, Yq / R=0.065286, C / R=0.188.

[0011] As an optimal technical solution for the above-mentioned multi-rotor aircraft propeller suitable for plateau areas, at r / R=40%, alpha, Yq / R and C / R satisfy: alpha=20.348°, Yq / R=0.062857, C / R=0.1801.

[0012] As an optimal technical solution for the above-mentioned multi-rotor aircraft propeller suitable for plateau areas, at r / R=50%, alpha, Yq / R and C / R satisfy: alpha=17.042°, Yq / R=0.05645, C / R=0.1573.

[0013] As an optimal technical solution for the above-mentioned multi-rotor aircraft propeller suitable for plateau areas, at r / R=60%, alpha, Yq / R and C / R satisfy: alpha=15.273°, Yq / R=0.05002, C / R=0.1365.

[0014] As an optimal technical solution for the above-mentioned multi-rotor aircraft propeller suitable for plateau areas, at r / R=70%, alpha, Yq / R and C / R satisfy: alpha=13.997°, Yq / R=0.043555, C / R=0.1162.

[0015] As an optimal technical solution for the above-mentioned multi-rotor aircraft propeller suitable for plateau areas, at r / R=80%, alpha, Yq / R and C / R satisfy: alpha=13.045°, Yq / R=0.0368, C / R=0.096.

[0016] The beneficial effects of the utility model are:

[0017] The utility model provides a propeller for a multi-rotor aircraft suitable for plateau areas, wherein the multi-rotor aircraft comprises a rotating shaft, the blades of the propeller are fixedly connected to the rotating shaft, and in a plane perpendicular to the axis of the rotating shaft of the propeller, the rotation center of the propeller is the origin of the coordinate axis, wherein the span direction is the direction from the root of the blade to the tip of the blade, that is, the direction of the X coordinate axis, the chord direction is the direction perpendicular to the span direction, that is, the direction of the Y coordinate axis, the airfoil is the inner profile of the cross section of the blade at any position in the span direction, and the distance between the leading edge and the trailing edge at the position of the airfoil is the wing The chord length of the airfoil is C, the angle between the chord line of the airfoil and the blade plane is the twist angle alpha, the perpendicular line from the propeller's center of rotation to the blade tip is L, the distance between the leading edge of the airfoil and L is Yq, and the distance between the propeller's center of rotation and the blade tip is R. At a distance of 35% R from the blade root, C, Yq, and alpha are all at their maximum values. From the blade root to the maximum chord length, C, alpha, and Yq all increase gradually, and from the maximum chord length to the blade tip, C, alpha, and Yq all decrease gradually. This configuration and the above-mentioned structural design effectively meet the requirements of multirotor aircraft for climbing and rapid maneuvering in plateau areas. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a schematic structural diagram of a propeller for a multi-rotor aircraft suitable for plateau areas provided by the utility model. DETAILED DESCRIPTION

[0019] The following describes in detail embodiments of the present invention. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present invention, and should not be construed as limiting the present invention.

[0020] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate the description of this utility model and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on this utility model. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. The terms "first position" and "second position" refer to two different positions.

[0021] Unless otherwise expressly specified or limited, the terms "mounted," "connected," "connect," and "fixed" should be interpreted broadly. For example, they may refer to fixed or removable connections; mechanical or electrical connections; direct or indirect connections through an intermediary; and internal communication between two components or the interaction between two components. Those skilled in the art will understand the specific meanings of these terms in this utility model based on specific circumstances.

[0022] Unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first feature being in direct contact with the second feature, or may include the first feature being in contact with the second feature through another feature between them instead of being in direct contact. Furthermore, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0023] The technical solution of the present invention will be further described below with reference to the accompanying drawings and through specific implementation methods.

[0024] like Figure 1As shown, this embodiment provides a propeller for a multi-rotor aircraft suitable for plateau areas, wherein the multi-rotor aircraft includes a rotating shaft, the propeller blades are fixedly connected to the rotating shaft, and in a plane perpendicular to the axis of the rotating shaft of the propeller, the rotation center of the propeller is the coordinate axis origin O, wherein the span direction is the direction from the blade root to the blade tip, that is, the X-axis direction, the chord direction is the direction perpendicular to the span direction, that is, the Y-axis direction, the airfoil is the cross-sectional profile of the blade at any position in the span direction, and the distance between the leading edge and the trailing edge at the position of the airfoil is The airfoil chord length C is the chord length of the airfoil, the angle of the airfoil chord relative to the blade rotor plane is the twist angle alpha, the vertical line from the propeller's center of rotation to the blade tip is L, the distance between the leading edge of the airfoil and L is Yq, and the distance between the propeller's center of rotation and the blade tip is R. At a distance of 35% R from the blade root, C, Yq, and alpha are all at their maximum values. From the blade root to the maximum chord length, C, alpha, and Yq all increase gradually, and from the maximum chord length to the blade tip, C, alpha, and Yq all decrease gradually. This configuration, employing the above structural design, can effectively meet the flight requirements of multirotor aircraft for climbing and rapid maneuvering in plateau areas.

[0025] Optionally, the cross-section where the airfoil is located is called the airfoil profile, and the distance between the airfoil profile and the center of rotation is r. It should be noted that C / R is the relative chord length of the corresponding position of the blade, a dimensionless parameter that can represent propellers of different diameters. r / R is the relative position of the cross-section where the airfoil is located, also a dimensionless parameter. Based on the above structural parameter setting method, the airfoil profile of the blade will not change when blades of different sizes are enlarged or reduced.

[0026] It should be noted that the specific ranges of C, Yq, alpha and r are as follows Figure 1 As shown in the mark.

[0027] This embodiment takes a 24.5-inch propeller as an example, and its structural design parameters are as follows:

[0028] Among them, at r / R=20%, alpha, Yq / R and C / R satisfy: alpha=6.3°, Yq / R=0.053, C / R=0.1348.

[0029] Optionally, at r / R=25%, alpha, Yq / R and C / R satisfy: alpha=12.599°, Yq / R=0.060952, C / R=0.1667.

[0030] Optionally, at r / R=30%, alpha, Yq / R and C / R satisfy: alpha=18.479°, Yq / R=0.065143, C / R=0.1839.

[0031] Optionally, at r / R=35%, alpha, Yq / R and C / R satisfy: alpha=20.998°, Yq / R=0.065286, C / R=0.188.

[0032] Optionally, at r / R=40%, alpha, Yq / R and C / R satisfy: alpha=20.348°, Yq / R=0.062857, C / R=0.1801.

[0033] Optionally, at r / R=50%, alpha, Yq / R and C / R satisfy: alpha=17.042°, Yq / R=0.05645, C / R=0.1573.

[0034] Optionally, at r / R=60%, alpha, Yq / R and C / R satisfy: alpha=15.273°, Yq / R=0.05002, C / R=0.1365.

[0035] Optionally, at r / R=70%, alpha, Yq / R and C / R satisfy: alpha=13.997°, Yq / R=0.043555, C / R=0.1162.

[0036] Optionally, at r / R=80%, alpha, Yq / R and C / R satisfy: alpha=13.045°, Yq / R=0.0368, C / R=0.096.

[0037] Optionally, at r / R=90%, alpha, Yq / R and C / R satisfy: alpha=11.421°, Yq / R=0.0285, C / R=0.076.

[0038] Optionally, at r / R=95%, alpha, Yq / R and C / R satisfy: alpha=8.979°, Yq / R=0.021047, C / R=0.0653.

[0039] Optionally, at r / R=100%, alpha, Yq / R and C / R satisfy: alpha=0°, Yq / R=0.004404, C / R=0.0474.

[0040] Obviously, the above embodiments of the present invention are merely examples for the purpose of clearly illustrating the present invention, and are not intended to limit the implementation methods of the present invention. Those skilled in the art will appreciate that other variations or modifications can be made based on the above description. It is not necessary and impossible to enumerate all implementation methods here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the claims of the present invention.

Claims

1. A propeller for multi-rotor aircraft suitable for plateau areas, characterized by: The blades of the propeller are fixedly connected to the rotating shaft, wherein the span direction is the direction from the blade root to the blade tip, the chord direction is the direction perpendicular to the span direction, the airfoil is the inner profile of the cross section of the blade at any position in the span direction, the distance between the leading edge and the trailing edge at the position of the airfoil is the chord length C of the airfoil, the angle between the chord line of the airfoil and the blade rotor plane is the torsion angle alpha, the vertical line between the rotation center of the propeller and the blade tip is L, the distance between the leading edge point of the airfoil and L is Yq, the distance between the rotation center of the propeller and the blade tip is R, and at a position 35% R from the blade root, C, Yq and alpha are all maximum values, and from the blade root to the maximum chord length position, C, alpha and Yq all gradually increase, and from the maximum chord length position to the blade tip, C, alpha and Yq all gradually decrease.

2. The multi-rotor aircraft propeller suitable for plateau areas according to claim 1, characterized in that: The cross section of the airfoil is called the airfoil section, and the distance between the airfoil section and the rotation center is r, wherein at r / R=20%, alpha, Yq / R and C / R satisfy: alpha=6.3°, Yq / R=0.053, C / R=0.1348.

3. The multi-rotor aircraft propeller suitable for plateau areas according to claim 2, characterized in that: in, At r / R=25%, alpha, Yq / R and C / R satisfy: alpha=12.599°, Yq / R=0.060952, C / R=0.1667.

4. The multi-rotor aircraft propeller suitable for plateau areas according to claim 2, characterized in that: in, At r / R=30%, alpha, Yq / R and C / R satisfy: alpha=18.479°, Yq / R=0.065143, C / R=0.1839.

5. The multi-rotor aircraft propeller suitable for plateau areas according to claim 2, characterized in that: in, At r / R=35%, alpha, Yq / R and C / R satisfy: alpha=20.998°, Yq / R=0.065286, C / R=0.

188.

6. The multi-rotor aircraft propeller suitable for plateau areas according to claim 2, characterized in that: in, At r / R=40%, alpha, Yq / R and C / R satisfy: alpha=20.348°, Yq / R=0.062857, C / R=0.1801.

7. The multi-rotor aircraft propeller suitable for plateau areas according to claim 2, characterized in that: in, At r / R=50%, alpha, Yq / R and C / R satisfy: alpha=17.042°, Yq / R=0.05645, C / R=0.1573.

8. The multi-rotor aircraft propeller suitable for plateau areas according to claim 2, characterized in that: in, At r / R=60%, alpha, Yq / R and C / R satisfy: alpha=15.273°, Yq / R=0.05002, C / R=0.1365.

9. The multi-rotor aircraft propeller suitable for plateau areas according to claim 2, characterized in that: in, At r / R=70%, alpha, Yq / R and C / R satisfy: alpha=13.997°, Yq / R=0.043555, C / R=0.1162.

10. The multi-rotor aircraft propeller suitable for plateau areas according to claim 2, characterized in that: in, At r / R=80%, alpha, Yq / R and C / R satisfy: alpha=13.045°, Yq / R=0.0368, C / R=0.096.

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