Paddle for rotor power system and rotor power system

Abstract

The utility model discloses a blade for a rotor wing power system and the rotor wing power system, and solves the technical problems that the lift force of an existing rotor wing is optimized by optimizing the angle of attack and / or the shape of the rotor wing, but the efficiency of the blade of the rotor wing needs to be improved. The paddle comprises a first paddle body and a second paddle body, the first paddle body and the second paddle body are in smooth connection with each other, the attack angle at the end of the first paddle body is a first attack angle alpha 1, and the attack angle at the joint of the first paddle body and the second paddle body is a second attack angle alpha 2, a first attack angle alpha 1 is formed at the end of the first paddle body, a second attack angle alpha 2 is formed at the end of the second paddle body, a third attack angle alpha 3 is formed at the end of the second paddle body, the angles of the first attack angle alpha 1, the second attack angle alpha 2 and the third attack angle alpha 3 are sequentially reduced, the first attack angle alpha 1 is 13-18 degrees, the second attack angle alpha 2 is 11-15 degrees, the third attack angle alpha 3 is 9-13 degrees, and the length L2 of the second paddle body is 1-3 times of the length L1 of the first paddle body. The utility model has the advantages of high bearing capacity and the like.

Description

Technical Field

[0001] The utility model relates to the technical field of rotor blades, in particular to a blade for a rotor power system and a rotor power system. Background Technique

[0002] A rotor blade is a slender wing surface connected to a rotor hub and generating aerodynamic force when rotating. It is an indispensable core component of various aircraft, responsible for providing lift and control force, and also playing a role similar to the ailerons and elevators of an airplane. The design and performance of the rotor are crucial for the flight quality of the aircraft, involving technologies including but not limited to rotor aerodynamic theory, structural design, flight control, etc. Its design and performance are directly related to the flight ability and safety of the helicopter. The angle of attack of the rotor is an important concept in aircraft flight. It involves the angle between the rotor blade and the relative airflow. This angle has a great influence on the lift and drag generated by the rotor and is a key parameter in flight performance analysis. In addition, in order to increase the lift generated by the rotor, in addition to designing the angle of attack of the rotor, the overall shape of the rotor is also designed. Currently, a reasonable design with a narrow inner width and a wide outer width can improve the lift of the rotor.

[0003] In the existing patent CN218477636U, it discloses a blade, a propeller and an aircraft for a rotor power system, including a blade root and a blade body. The blade body includes a connecting part and a main body part; the blade root, the connecting part and the main body part are connected in sequence; at the first position of the connection, the first position of the main body part, and the second position of the main body part, the angles of attack of the blade are the first angle of attack, the second angle of attack and the third angle of attack respectively, and these three positions are arranged along the length direction of the blade; the first angle of attack is less than the second angle of attack, and the second angle of attack is greater than the third angle of attack. The propeller includes a propeller hub and a blade, and the blade is connected to the propeller hub through the blade root. In this device, the blade profile at the connection between the blade root and the blade body is improved, so that the connection between the blade root and the blade body is smooth, the structural strength of the blade is improved, the blade is not easily deformed during use, and the blade is not easily broken near the root of the blade root; the blade is not easily deformed or broken even when the size is increased.

[0004] In the existing patent CN205770151U, it discloses a drone rotor. The width of the rotor gradually increases from the outer free end to the inner end in the length direction, forming a structure with a narrow outer side and a wide inner side, and then gradually decreases to form a conical connecting part with an arc-shaped head. And the thickness of the rotor from one side end to the other side end in the width direction gradually increases with a large smooth arc surface to a certain position, and then the thickness is gradually decreased through a small smooth arc surface and transitions to the other side end to form a streamlined surface. Through the optimized rotor structure, the lift efficiency of the rotor is improved, the operating resistance is reduced, the load capacity of the multi-rotor drone is greatly improved, and the flight efficiency is effectively improved.

[0005] However, in existing patents, only the optimization of rotor lift by changing the rotor blade angle of attack and / or shape is considered. However, the lift improvement brought by this is limited, and the blade efficiency is not considered. Based on the above problems, the present utility model proposes a blade for a rotor power system to solve the above problems. Summary of the Utility Model

[0006] The technical problem to be solved by the present utility model is: the existing rotor optimizes the rotor lift by optimizing the rotor blade angle of attack and / or shape, but the lift is limited and the efficiency of the rotor blade needs to be improved.

[0007] The present utility model is realized by the following technical solutions:

[0008] A blade for a rotor power system, comprising:

[0009] A first blade body and a second blade body, the first blade body and the second blade body are smoothly connected to each other. The angle of attack at the end of the first blade body is the first angle of attack α1, the angle of attack at the connection between the first blade body and the second blade body is the second angle of attack α2, and the angle of attack at the end of the second blade body is the third angle of attack α3. The angles of the first angle of attack α1, the second angle of attack α2, and the third angle of attack α3 decrease in sequence.

[0010] The first angle of attack α1 is 13° - 18°, the second angle of attack α2 is 11° - 15°, and the third angle of attack α3 is 9° - 13°.

[0011] The length L2 of the second blade body is 1 - 3 times the length L1 of the first blade body.

[0012] In the present utility model, by dividing the blade as a whole into three different angles of attack, it can be optimized for different stages and conditions during flight, adapt to different flight states of the aircraft, improve the blade efficiency and flight performance. In addition, it should be noted that by designing the lengths of the second blade body and the first blade body, the lift effect is further optimized. This setting, combined with the first angle of attack α1, the second angle of attack α2, and the third angle of attack α3, further improves the blade load-bearing capacity.

[0013] Further, the width of the first blade body gradually increases from the end to the connection with the second blade body, and the width of the second blade body gradually decreases from the connection with the first blade body to the end, forming a structure that is wider inside and narrower outside.

[0014] After adopting this technical solution, it should be noted that by optimizing the shapes of the first blade body and the second blade body, the overall blade forms a structure that is wider inside and narrower outside. The design of the blade being wider inside and narrower outside can achieve a relatively high blade efficiency at different angles of attack, thereby improving the efficiency of the rotor. Coupled with the design of setting three angles of attack at the end of the first blade body, the connection part of the first blade body and the second blade body, and the end of the second blade body, the blade efficiency is further optimized.

[0015] Preferably, the length L2 of the second blade body is twice the length L1 of the first blade body.

[0016] After adopting this technical solution, it should be noted that the length L2 of the second blade body is two-thirds of the blade length, that is, the length of the wider inner section of the blade is half of the length of the narrower outer section of the blade. Through this setting, the efficiency of the rotor blade is further optimized. Coupled with the setting of three angles of attack, the blade efficiency is further improved.

[0017] Preferably, the first angle of attack α1 is equal to 15°, the second angle of attack α2 is equal to 13°, and the third angle of attack α3 is equal to 11°.

[0018] After adopting this technical solution, it should be noted that by setting the first angle of attack α1 equal to 15°, the second angle of attack α2 equal to 13°, and the third angle of attack α3 equal to 11°, the performance requirements for the drive device are lower, and a relatively large lift can be generated and good blade efficiency can be maintained even when the performance of the drive device is not high.

[0019] Preferably, the aspect ratio of the blade is 4.5 - 9.5. The aspect ratio is the ratio of the blade span to the chord length. The blade span refers to the lateral width of the blade, and the chord length is the straight-line distance between the leading edge and the trailing edge of the blade.

[0020] Preferably, the end of the first blade body is used to connect a drive device, such as a motor shaft, etc., to drive the blade to rotate. When used to generate lift, at least two blades are connected to the drive device, and the blades are symmetrically arranged to ensure the normal generation of lift.

[0021] The utility model has the following advantages and beneficial effects:

[0022] 1. The utility model designs a blade for a rotor power system. By dividing the blade as a whole into three angles of attack that change sequentially, it can be optimized for different stages and conditions during flight, adapt to different flight states of the aircraft, and improve the blade efficiency and flight performance.

[0023] 2. By optimizing the shapes of the first blade body and the second blade body, the present utility model makes the overall blade form a structure that is wider inside and narrower outside. Together with the design of setting three angles of attack at the end of the first blade body, the connection part of the first blade body and the second blade body, and the end of the second blade body, the blade efficiency is further optimized.

[0024] 3. By setting the length L2 of the second blade body to two-thirds of the blade length, that is, the length of the wider inner part of the blade is half of the length of the narrower outer part of the blade, the present utility model further optimizes the efficiency of the rotor blade. Together with the setting of three angles of attack, the blade efficiency is further improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The drawings described herein are used to provide a further understanding of the embodiments of the present utility model, form a part of the present utility model, and do not limit the embodiments of the present utility model. In the drawings:

[0026] Figure 1 is a schematic diagram of the assembled structure of two blades of the present utility model;

[0027] Figure 2 is a schematic diagram of the blade structure of the present utility model;

[0028] Figure 3 is a side view of the first blade body of the present utility model;

[0029] Figure 4 is a cross-sectional view of the connection part of the first blade body and the second blade body of the present utility model;

[0030] Figure 5 is a side view of the second blade body of the present utility model.

[0031] The names of the components in the drawings are as follows:

[0032] 1 - blade, 101 - first blade body, 102 - second blade body. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0033] To make the objectives, technical solutions, and advantages of the present utility model clearer and more understandable, the present utility model will be further described in detail below in combination with the embodiments and the drawings. The illustrative embodiments and descriptions thereof of the present utility model are only used to explain the present utility model and do not limit the present utility model.

[0034] As Figures 1 - 5 shown, a blade for a rotor power system, as Figure 1 , Figure 2 shown, includes:

[0035] A first blade body 101 and a second blade body 102, the first blade body 101 and the second blade body 102 are smoothly connected to each other,

[0036] The angle of attack at the end of the first blade body 101 is the first angle of attack α1, the angle of attack at the connection between the first blade body 101 and the second blade body 102 is the second angle of attack α2, and the angle of attack at the end of the second blade body 102 is the third angle of attack α3. The angles of the first angle of attack α1, the second angle of attack α2, and the third angle of attack α3 decrease in this order. The first angle of attack α1 is 13° - 18°, the second angle of attack α2 is 11° - 15°, and the third angle of attack α3 is 9° - 13°. The length L2 of the second blade body 102 is 1 - 3 times the length L1 of the first blade body 101, and the aspect ratio of the blade is 4.5 - 9.5.

[0037] In another embodiment of the present invention, as Figure 1 , Figure 2 shown, the width of the first blade body 101 gradually increases from the end to the connection with the second blade body 102, and the width of the second blade body 102 gradually decreases from the connection with the first blade body 101 to the end, forming a structure that is wider inside and narrower outside. The design of the rotor being wider inside and narrower outside and the length matching of different blade bodies can improve the blade efficiency. Combining with the design of setting three angles of attack at the end of the first blade body 101, the connection part of the first blade body 101 and the second blade body 102, and the end of the second blade body 102 further optimizes the blade efficiency. The simulation results also verify that under the same other parameters such as the required torque and rotational speed, the blade efficiency of the above structure is higher than others.

[0038] In another embodiment of the present invention, as Figure 2 shown, the length L2 of the second blade body 102 is 2 times the length L1 of the first blade body 101, that is, the length L1 of the first blade body 101 is one-third of the blade length of blade 1, and the length L2 of the second blade body 102 is two-thirds of the blade length. That is, the length of the wider inner section of blade 1 is half of the length of the narrower outer section of blade 1. By this setting, the rotor blade efficiency is further optimized. Combining with the three angles of attack settings, the blade efficiency is further improved.

[0039] In another embodiment of the present invention, as Figures 3 - 5 shown, the first angle of attack α1 is equal to 15°, the second angle of attack α2 is equal to 13°, and the third angle of attack α3 is equal to 11°. By setting the first angle of attack α1 to 15°, the second angle of attack α2 to 13°, and the third angle of attack α3 to 11°, the performance requirements for the drive device are lower, and a relatively large lift can be generated even when the performance of the drive device is not high, and good efficiency of blade 1 can be maintained. The simulation results also verify that under the same other parameters such as the required torque and rotational speed, the blade efficiency of the above structure is higher than others.

[0040] The end of the first blade body 101 is used to connect to the drive device.

[0041] The present utility model discloses a rotor power system, which includes the above-mentioned blade, and connects at least two blades to the rotating shaft of the motor for generating lift by rotation.

[0042] In the present utility model, the blade efficiency refers to the ratio of the lift force to the required torque.

[0043] In the above specific embodiments, the purpose, technical solution and beneficial effects of the present utility model are further described in detail. It should be understood that the above is only the specific embodiment of the present utility model and is not used to limit the protection scope of the present utility model. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model shall be included in the protection scope of the present utility model.

Claims

1. A blade for a rotor power system, characterized in that, Comprising: A first blade body (101) and a second blade body (102), the first blade body (101) and the second blade body (102) being smoothly connected to each other, The angle of attack at the end of the first blade body (101) is the first angle of attack α1, the angle of attack at the connection between the first blade body (101) and the second blade body (102) is the second angle of attack α2, the angle of attack at the end of the second blade body (102) is the third angle of attack α3, and the angles of the first angle of attack α1, the second angle of attack α2, and the third angle of attack α3 decrease in sequence, The first angle of attack α1 is 13° - 18°, the second angle of attack α2 is 11° - 15°, and the third angle of attack α3 is 9° - 13°, The length L2 of the second blade body (102) is 1 - 3 times the length L1 of the first blade body (101).

2. The blade for a rotor power system according to claim 1, characterized in that, The width of the first blade body (101) gradually increases from the end to the connection with the second blade body (102), and the width of the second blade body (102) gradually decreases from the connection with the first blade body (101) to the end, forming a structure that is wider inside and narrower outside.

3. The one according to claim 1, characterized in that, The length L2 of the second blade body (102) is 2 times the length L1 of the first blade body (101).

4. A blade for a rotor power system according to any one of claims 1-3, characterized in that, The first angle of attack α1 is equal to 15°, the second angle of attack α2 is equal to 13°, and the third angle of attack α3 is equal to 11°.

5. A blade for a rotor power system according to any one of claims 1 - 3, characterized in that, The aspect ratio of the blade is 4.5 - 9.

5.

6. A blade for a rotor power system according to any one of claims 1-3, characterized in that, The end of the first blade body (101) is used to connect to the drive device.

7. A rotor power system, characterized in that Comprising a blade for a rotor power system as described in any one of claims 1 - 6.

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