Negative pressure and thrust dual-purpose propeller structure

Abstract

This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a dual-purpose (negative pressure and thrust) propeller structure. The propeller includes a shaft core, and for use by a flying robot capable of adhering to a vertical wall surface, the propeller has two large-radius blades and several smaller-radius blades arranged on the outer wall of the shaft core. The two large-radius blades are symmetrically arranged at 180 degrees along the shaft core. By adding several smaller-radius blades to optimize the design, compared to traditional propellers, this design improves airflow distribution and eliminates the problem of low airflow velocity near the shaft core during negative pressure adsorption and flight; it also enhances the ventilation effect, especially in the semi-enclosed negative pressure chamber, achieving better air circulation.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle technology, specifically to a propeller structure that can be used for both negative pressure and thrust. Background Technology

[0002] Traditional aircraft propeller designs typically focus on providing thrust without emphasizing airflow or performance within the negative pressure chamber. Because the linear velocity near the shaft core is lower than in other areas, thrust is weaker, and airflow is also less efficient.

[0003] 1. Uneven airflow distribution: Near the shaft core, the airflow speed is low, which may lead to uneven airflow distribution, thus affecting the thrust of the aircraft.

[0004] 2. Insufficient ventilation: Traditional designs may not provide sufficient ventilation in the negative pressure chamber, especially in semi-enclosed environments, where good airflow circulation may not be achieved.

[0005] 3. Performance balance issue: As an amphibious flying robot, the special aerodynamic and power requirements of the adsorption flying robot may require more innovative designs, and traditional designs may not be able to meet these requirements. Summary of the Invention

[0006] (a) Technical problems to be solved

[0007] This invention addresses the above-mentioned problems by proposing a propeller structure that combines negative pressure and thrust. Its purpose is to solve the problems of uneven airflow distribution, insufficient ventilation effect, and performance balance of traditional propellers.

[0008] (II) Technical Solution

[0009] To achieve the above objectives, the present invention provides a propeller structure for both negative pressure and thrust, including a propeller shaft core. The propeller, which is used for mounting on a flying robot that can adhere to a vertical wall, has two large-radius blades and several first small-radius blades arranged on the outer wall of the shaft core. The two large-radius blades are arranged symmetrically at 180 degrees along the shaft core.

[0010] Furthermore, the large-radius blade has a hole at the root near the shaft core.

[0011] Furthermore, the shaft core is provided with a second small-radius blade along the same axis, and the second small-radius blade is located at the lower end of the first small-radius blade.

[0012] Furthermore, the large-radius blade, the first small-radius blade, and the second small-radius blade are all made of lightweight, wear-resistant materials.

[0013] Furthermore, the first small-radius blade has a leading-edge serrated structure. The leading-edge serrated structure includes a recess and a protrusion at the outermost position of the leading edge of the first small-radius blade. The recess extends continuously from the root near the shaft core along the span direction of the first small-radius blade to the protrusion. The recess occupies 3 / 2 of the span of the first small-radius blade, and the protrusion occupies 3 / 1 of the span of the first small-radius blade.

[0014] Furthermore, the holes are circular and their number is an array.

[0015] Furthermore, the large-radius blade and the first small-radius blade are flat or curved.

[0016] Furthermore, the distance between the large-radius blade and the first small-radius blade ranges from 10 to 50 millimeters.

[0017] Furthermore, the spacing between the first small-radius blade and the second small-radius blade ranges from 20 to 60 millimeters.

[0018] Furthermore, the number of the first small-radius blades is 10-15, and the first small-radius blades are between one-quarter and one-half of the radius of the larger-radius blade.

[0019] (III) Beneficial Effects

[0020] This invention provides a dual-purpose propeller structure for both negative pressure and thrust, optimized by adding several first-small-radius blades. Compared to traditional propellers, this design achieves the following effects under negative pressure adsorption and flight conditions: improved airflow distribution, eliminating the problem of low airflow velocity near the shaft core; enhanced ventilation, especially in the semi-enclosed negative pressure chamber, achieving better air circulation; balanced thrust and ventilation to ensure that different aerodynamic and power requirements are met; and improved endurance while reducing adsorption rotation speed requirements. This innovative design provides a stronger ventilation effect and performance optimization for the operating environment of adsorption-type amphibious flying robots, exhibiting significant differentiation and application value. Attached Figure Description

[0021] Figure 1 This is a rendering of the actual effect of a dual-purpose propeller structure for negative pressure and thrust disclosed in this application.

[0022] Figure 2 This is a top view of a dual-purpose propeller structure for both negative pressure and thrust disclosed in this application.

[0023] Figure 3 This is a front view of a dual-purpose propeller structure for both negative pressure and thrust disclosed in this application.

[0024] Figure 4 This is a schematic diagram of the structure of a first small-radius blade disclosed in this application.

[0025] The reference numerals in the figure are as follows: 1. Shaft core; 2. Large radius blade; 3. First small radius blade; 4. Second small radius blade; 5. Leading edge serrated structure; 101. Hole; 501. Recess; 502. Protrusion. Detailed Implementation

[0026] The present invention will now be described in detail with reference to the accompanying drawings, and the technical solutions in the embodiments of the present invention will be clearly and completely described. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0027] It should be noted that when a component is described as "fixed to" another component, it can be directly on the other component or may have a component in between. When a component is considered "connected to" another component, it can be directly connected to the other component or may have a component in between. When a component is considered "set on" another component, it can be directly set on the other component or may have a component in between. The terms "vertical," "horizontal," "left," "right," and similar expressions used in this document are for illustrative purposes only.

[0028] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0029] Please see Figures 2-3 The diagram shown is a structural diagram of a dual-purpose propeller for both negative pressure and thrust, provided in a preferred embodiment of this application. Figures 2-3 In the embodiment shown, a propeller shaft 1 is included. The propeller used by the flying robot that can be mounted on a vertical wall has two large-radius blades 2 and several first small-radius blades 3 arranged on the outer wall of the shaft 1. The two large-radius blades 2 are arranged symmetrically at 180 degrees along the shaft.

[0030] exist Figure 1The diagram shows the vertical velocities of airflow through the two propellers in hovering and suction modes. The curves represent airflow direction, and the curve lengths represent airflow velocity. Traditional propellers can lead to uneven airflow distribution, especially near the shaft core 1. This design adjusts the airflow distribution and improves the overall aerodynamic performance of the aircraft by combining blades of different sizes. By adding a first small-radius blade 3 to the propeller, this design significantly enhances the suction effect near the shaft core 1. This achieves better airflow circulation in environments such as semi-enclosed negative pressure chambers, helping to maintain a high negative pressure state and improve the robot's adsorption strength. Furthermore, this design provides sufficient propulsion while also enhancing the suction effect. This performance balance allows the robot to achieve better overall performance in both propulsion and airflow circulation. Because this design offers better suction and airflow circulation, the robot's adsorption strength is improved, the adsorption speed requirement is reduced, and the endurance is increased.

[0031] The above components will be described in detail below.

[0032] Two large-radius blades 2 and several small-radius blades 3 are arranged on the outer wall of the propeller shaft core 1. These blades are arranged symmetrically at 180 degrees, with holes 101 formed in the large-radius blades 2 near the root of the shaft core 1. Part of the airflow can directly enter the propeller interior through the holes 101, increasing the airflow velocity near the shaft core 1 and improving airflow distribution. For the negative pressure chamber, the holes 101 allow more gas to enter, enhancing the ventilation effect in the area near the shaft core 1 and helping to create a stable low-pressure environment.

[0033] In addition to the large-radius blade 2 and the first small-radius blade 3, the shaft core 1 also has a second small-radius blade 4 arranged along the same axis, located below the first small-radius blade 3. The second small-radius blade 4 further enhances the suction effect and strengthens the airflow dynamics, especially near the shaft core 1. They can improve airflow circulation and maintain a high negative pressure state in environments such as semi-enclosed negative pressure chambers, thereby increasing the robot's adsorption strength.

[0034] The large-radius blade 2, the first small-radius blade 3, and the second small-radius blade 4 are all made of lightweight and wear-resistant materials to ensure their strength and durability.

[0035] In addition, such as Figure 4As shown, the first small radius blade 3 has a leading edge serrated structure 5. Specifically, the leading edge serrated structure 5 is located at the outermost position of the leading edge of the first small radius blade 3. It can be understood that the outermost position is the blade tip region along the span direction, including a recess 501 and a protrusion 502. The recess 501 extends continuously from the root near the shaft core 1 along the span direction of the first small radius blade 3 to the position of the protrusion 502. The recess 501 occupies 3 / 2 of the span of the first small radius blade 3, and the protrusion 502 occupies 3 / 1 of the span of the first small radius blade 3.

[0036] In this embodiment, the protrusions 502 provide an obstacle between the flight airflow and the surface of the first small-radius blade 3, inducing turbulence and altering the direction and velocity of the airflow. They can be sharp, rounded, or other shapes to produce the desired turbulence effect. The recesses 501 are connected to the protrusions 502, contributing to the formation of turbulent regions. The purpose is to induce turbulence in the airflow entering the first small-radius blade 3 and change its direction and velocity. By introducing turbulence, the leading-edge serrated structure 5 can effectively reduce the impact of lateral airflow on the first small-radius blade 3, improving flight stability and control performance.

[0037] The spacing between the large-radius blade 2 and the first small-radius blade 3 typically ranges from 10 to 50 mm, while the spacing between the first small-radius blade 3 and the second small-radius blade 4 typically ranges from 20 to 60 mm. Furthermore, the number of first small-radius blades 3 is typically 10 to 15, and their length is approximately one-quarter to one-half the radius of the large-radius blade 2. This design provides sufficient thrust and optimizes airflow circulation, achieving a balance in overall performance.

[0038] Through the aforementioned design features, the propeller of this flying robot can improve airflow distribution, enhance ventilation effect, increase adsorption intensity, and possess good propulsion and airflow circulation performance, thereby reducing the adsorption speed requirement and improving endurance.

[0039] It will be apparent to those skilled in the art that this application is not limited to the details of the exemplary embodiments described above, and that this application can be implemented in other specific forms without departing from the spirit or essential characteristics of this application. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of this application is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be embraced within this application. No reference numerals in the claims should be construed as limiting the scope of the claims. Furthermore, it is clear that the word "comprising" does not exclude other units or steps, and the singular does not exclude the plural. Multiple units or devices recited in the apparatus claims may also be implemented by the same unit or device in software or hardware. The terms "first," "second," etc., are used to indicate names and do not indicate any particular order.

[0040] The above embodiments are only used to illustrate the technical solutions of this application and are not intended to limit it. Although this application has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of this application without departing from the spirit and scope of the technical solutions of this application.

Claims

1. A propeller structure for both negative pressure and thrust, characterized in that, The propeller includes a shaft core for use by a flying robot that can be mounted on a vertical wall. The outer wall of the shaft core has two large-radius blades and several first small-radius blades. The two large-radius blades are symmetrically arranged at 180 degrees along the shaft core. The first small-radius blades have a leading-edge serrated structure. The leading-edge serrated structure is located at the outermost position of the leading edge of the first small-radius blade and includes a recess and a protrusion. The recess extends continuously from the root near the shaft core along the span of the first small-radius blade to the protrusion. The recess occupies 2 / 3 of the span of the first small-radius blade, and the protrusion occupies 1 / 3 of the span of the first small-radius blade.

2. A negative pressure and thrust dual propeller structure according to claim 1, characterized in that, The large-radius blade has a hole at its root near the shaft core.

3. The negative pressure and thrust dual propeller structure according to claim 2, characterized in that, The shaft core is provided with a second small-radius blade along the same axis, and the second small-radius blade is located at the lower end of the first small-radius blade.

4. The negative pressure and thrust dual propeller structure according to claim 3, characterized in that, The large-radius blade, the first small-radius blade, and the second small-radius blade are all made of lightweight and wear-resistant materials.

5. The negative pressure and thrust dual propeller structure according to claim 2, characterized in that, The holes are circular and number in an array.

6. The dual-purpose propeller structure for negative pressure and thrust according to claim 1, characterized in that, The large-radius blade and the first small-radius blade are flat or curved.

7. The negative pressure and thrust dual propeller structure according to claim 1, characterized in that, The distance between the large-radius blade and the first small-radius blade ranges from 10 to 50 millimeters.

8. The negative pressure and thrust dual propeller structure according to claim 1, characterized in that, The spacing between the first small-radius blade and the second small-radius blade ranges from 20 to 60 millimeters.

9. The negative pressure and thrust dual propeller structure according to claim 1, characterized in that, The number of the first small radius blades is 10-15, and the first small radius blades are between one-quarter and one-half of the radius of the larger radius blade.

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