Propeller blade of aircraft and aircraft

Abstract

The utility model relates to the technical field of aircrafts, and discloses a propeller blade of an aircraft and the aircraft.The propeller blade of the aircraft comprises a box-shaped beam body module arranged in the length direction of the propeller blade; the first side supporting structure is arranged on one side of the box-shaped beam body module, is arranged in the length direction of the box-shaped beam body module and is attached to the box-shaped beam body module; the second side supporting structure is arranged on the other side of the box-shaped beam body module, arranged in the length direction of the box-shaped beam body module and attached to the box-shaped beam body module. And the wing surface skin covers the outer surfaces of the first side supporting structure and the second side supporting structure. The propeller blade has the advantages that the propeller blade is high in strength, reasonable in structural design and convenient to form, and enough strength of the propeller blade can be guaranteed when the propeller blade is very thin.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a propeller blade and an aircraft. Background Technology

[0002] Propeller blades are one of the core components of an aircraft propulsion system. During operation, they rotate at high speeds, interact with the air, and generate lift. Composite materials have high specific strength and specific stiffness, and are lightweight, so they are widely used in propeller blades.

[0003] Existing composite propeller blades mainly consist of an internal foam core and an outer skin covering the outer surface of the foam core. When the propeller blade is made very thin, the strength of the foam core is poor, making it difficult to meet the usage requirements. Furthermore, the existing composite propeller blade molding process is complex and difficult to mold. Utility Model Content

[0004] In view of the above-mentioned shortcomings of the existing technology, the technical problem to be solved by this utility model is to provide a propeller blade for an aircraft with high strength, reasonable structural design and convenient molding, as well as an aircraft.

[0005] The technical solution adopted by this utility model to solve its technical problem is to propose a propeller blade for an aircraft, comprising:

[0006] The box-shaped beam module is arranged along the length of the propeller blade;

[0007] A first side support structure and a second side support structure are provided. The first side support structure is disposed on one side of the box-shaped beam module and is arranged along the length direction of the box-shaped beam module, and is attached to the box-shaped beam module. The second side support structure is disposed on the other side of the box-shaped beam module and is arranged along the length direction of the box-shaped beam module, and is attached to the box-shaped beam module.

[0008] The wing skin covers the outer surfaces of the first side support structure and the second side support structure.

[0009] Furthermore, the box-shaped beam module includes an upper beam and a lower beam disposed below the upper beam and attached to the upper beam;

[0010] The first side support structure is located on the left side of both the upper beam and the lower beam, and is attached to both; the second side support structure is located on the right side of both, and is attached to both.

[0011] Furthermore, a groove is provided on the lower beam or between the lower beam and the upper beam, near the root of the propeller blade, and a counterweight is provided in the groove.

[0012] Furthermore, both the first side support structure and the second side support structure are hollow.

[0013] Furthermore, the wing skin includes an upper skin and a lower skin, with the lower skin covering the area below the first side support structure and the second side support structure, and the upper skin covering the area above the first side support structure and the second side support structure.

[0014] Furthermore, one or more of the upper beam, the lower beam, the upper skin, and the lower skin are formed by carbon fiber 3D printing.

[0015] Furthermore, a metal blade holder is provided at the root of the propeller blade, and the metal blade holder is cylindrical in shape.

[0016] Furthermore, the propeller blade has a protrusion at one end near the propeller root, and the cross-sectional areas of the box-shaped beam module, the first side support structure, and the second side support structure gradually decrease from the protrusion towards the end away from the propeller root.

[0017] Furthermore, the box-shaped beam module, the first side support structure, the second side support structure, and the wing skin are integrally formed by reaction injection molding of polyurethane material.

[0018] The technical solution adopted by this utility model to solve its technical problem is to also propose an aircraft, including a plurality of the above-mentioned propeller blades.

[0019] Compared with the prior art, the present invention has at least the following beneficial effects:

[0020] (1) In this utility model, a box-shaped beam module is provided between the first side support structure and the second side support structure in the propeller blade. This box-shaped beam module can effectively ensure that the propeller blade has sufficient strength, and the first side support structure and the second side support structure can replace the filling foam in traditional composite material propeller blades. Furthermore, even when the propeller blade is made very thin, its strength can still be guaranteed. When the propeller blade is relatively thick, it does not affect the use of filling foam.

[0021] (2) In this utility model, the upper beam, lower beam and upper skin of the box-shaped beam body and the lower skin of the wing skin, as well as the first side support structure and the second side support structure, can all be formed by 3D printing, which is convenient to form, and the overall stability of the propeller blade is good.

[0022] (3) In this utility model, both the first side support structure and the second side support structure are hollow. Under the condition of ensuring sufficient strength, the first side support structure and the second side support structure are hollow, which can effectively reduce the mass of the first side support structure and the second side support structure and facilitate the realization of lightweighting. Attached Figure Description

[0023] Figure 1 This is an exploded view of the propeller blade of this utility model;

[0024] Figure 2 A schematic diagram of the structure of a propeller blade after the airfoil skin has been removed;

[0025] Figure 3 This is a cross-sectional view of the propeller blades.

[0026] In the picture:

[0027] 1. Upper beam; 2. Lower beam; 3. First side support structure; 4. Second side support structure; 5. Upper skin; 6. Lower skin; 7. Counterweight; 8. Metal blade; 9. Polyurethane; 10. Protrusion. Detailed Implementation

[0028] The following are specific embodiments of the present invention, which are described in conjunction with the accompanying drawings. However, the present invention is not limited to these embodiments.

[0029] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in this utility model embodiment are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.

[0030] Furthermore, in this utility model, the use of terms such as "first," "second," and "a" is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this utility model, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0031] In this utility model, unless otherwise explicitly specified and limited, the terms "connection," "fixing," etc., should be interpreted broadly. For example, "fixing" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0032] Furthermore, the technical solutions of the various embodiments of this utility model can be combined with each other, but only if they are based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by this utility model.

[0033] like Figures 1-3 As shown, a propeller blade for an aircraft mainly includes: a box-shaped beam module, a first side support structure 3, a second side support structure 4, and a wing skin.

[0034] The box-shaped beam module is arranged along the length of the propeller blade, from the root end of the propeller blade to the shaft end, in order to improve the strength of the propeller blade. Even if the propeller blade is very thin, the box-shaped beam module can ensure that it has sufficient strength. When the propeller blade is thicker, foam can be placed inside it.

[0035] In this embodiment, the box-shaped beam module includes an upper beam 1 and a lower beam 2 disposed below and attached to the upper beam 1. Dividing the box-shaped beam module into an upper beam 1 and a lower beam 2 facilitates manufacturing.

[0036] The first side support structure 3 is located on one side of the box-shaped beam module and is positioned along the length of the box-shaped beam module, in close contact with it. The second side support structure 4 is located on the other side of the box-shaped beam module and is positioned along the length of the box-shaped beam module, in close contact with it. Specifically, the first side support structure 3 is located on the left side of both the upper beam 1 and the lower beam 2, and is in close contact with them; the second side support structure 4 is located on the right side of both, and is in close contact with them.

[0037] In this embodiment, both the first side support structure 3 and the second side support structure 4 are hollow. That is, under the condition of ensuring sufficient strength, the first side support structure 3 and the second side support structure 4 are hollow, which can effectively reduce the mass of the first side support structure 3 and the second side support structure 4, thus facilitating weight reduction.

[0038] The wing skin covers the outer surfaces of the first side support structure 3 and the second side support structure 4. Specifically, the wing skin in this embodiment includes an upper skin 5 and a lower skin 6. The lower skin 6 covers the lower part of the first side support structure 3 and the second side support structure 4, and the upper skin 5 covers the upper part of the first side support structure 3 and the second side support structure 4.

[0039] After the lower beam 2, counterweight, upper beam 1, first side support structure 3, second side support structure 4, lower skin 6, and upper skin 5 are assembled, they are placed in a mold and injection molded into one piece using polyurethane 9 material to ensure the overall structural stability and prevent parts from separating during use.

[0040] Specifically, in this embodiment, a groove is provided on the lower beam 2 or between the lower beam 2 and the upper beam 1, near the root of the propeller blade. A counterweight 7 is provided in the groove. The counterweight 7 is a counterweight tube. That is, a cylindrical groove is formed between the upper beam 1 and the lower beam 2 to accommodate the installation of the counterweight tube.

[0041] A metal blade holder 8 is provided at the root of the propeller blade, and the metal blade holder 8 is cylindrical. A protrusion 10 is provided at the end of the propeller blade near the root. The cross-sectional area of ​​the box-shaped beam module, the first side support structure 3, and the second side support structure 4 gradually decreases from the protrusion 10 to the end away from the root. The protrusion 10 makes the upper beam 1, the lower beam 2, the first side support structure 3, and the second side support structure 4 larger at this location, ensuring sufficient strength when the propeller blade rotates at high speed.

[0042] Among them, the upper beam 1, lower beam 2, upper skin 5 and lower skin 6 can all be formed by carbon fiber 3D printing.

[0043] In practical use, a box-shaped beam module is installed between the first side support structure 3 and the second side support structure 4 in the propeller blade. This box-shaped beam module effectively ensures sufficient strength of the propeller blade, and the first side support structure 3 and the second side support structure 4 can replace the filling foam in traditional composite material propeller blades. Furthermore, even when the propeller blade is very thin, its strength is still guaranteed. Similarly, when the propeller blade is thicker, the use of filling foam is not affected.

[0044] Among them, the upper beam 1 and lower beam 2 of the box-shaped beam, the upper skin 5 and lower skin 6 of the wing skin, as well as the first side support structure 3 and the second side support structure 4 can all be formed by 3D printing, which is convenient and the propeller blade has good overall stability.

[0045] The upper beam 1 and lower beam 2 are arranged vertically, the first side support structure 3 and the second side support structure 4 are arranged horizontally, and the upper skin 5 and lower skin 6 are arranged vertically. The structural layout and setting are reasonable.

[0046] Specifically, the propeller blades of this embodiment can be formed by the following method:

[0047] Based on the three-dimensional digital model of the propeller blade, the lower beam 2 of the box-shaped beam module was 3D printed.

[0048] The counterweight 7 is formed at the root of the paddle and installed in the groove of the lower beam 2; wherein, the counterweight 7 is cut by CNC process and the counterweight tube is 3D printed in the groove of the lower beam 2 using high density material.

[0049] Based on the three-dimensional digital model of the propeller blade, the upper beam 1 is 3D printed and combined with the counterweight 7 and the lower beam 2. The specific 3D printing methods for the upper beam 1 and the lower beam 2 are as follows: the upper beam 1 and the lower beam 2 are printed using a continuous carbon fiber filament 3D printer; and the box-shaped beam module is thermoset using an autoclave.

[0050] By replacing the printhead, a first side support structure 3 and a second side support structure 4 of a hollow structure are 3D printed on the surface of the box-shaped beam module using lightweight plastic filaments. This structure can replace the role of filling foam in traditional blade manufacturing.

[0051] Install the metal blade shank at the blade root 8.

[0052] Molded blade airfoil skin, and then covered with airfoil skin;

[0053] Specifically, the wing skin forming methods are as follows: forming the upper skin 5 and lower skin 6 using a carbon fiber cloth lamination process, and then laying and molding them; forming the upper skin 5 and lower skin 6 using Automatic Tape Laying (ATL) technology, and then laying and molding them; using a continuous carbon fiber filament 3D printer to wind and print an integral wing skin on the first side support structure 3 and the second side support structure 4; and using Automatic Fiber Placement (AFP) technology to continuously wind and lay the wing skin on the first side support structure 3 and the second side support structure 4.

[0054] The upper beam 1, lower beam 2, counterweight 7, first side support structure 3, second side support structure 4, and wing skin are placed in the mold and injection molded into a whole using polyurethane 9 material.

[0055] In this design, the propeller blade has high strength, a reasonable structural design, and is easy to form. Even when the propeller blade is made very thin, it can still have sufficient strength.

Claims

1. A propeller blade for an aircraft, characterized in that include: The box-shaped beam module is arranged along the length of the propeller blade; A first side support structure and a second side support structure are provided. The first side support structure is disposed on one side of the box-shaped beam module and is arranged along the length direction of the box-shaped beam module, and is attached to the box-shaped beam module. The second side support structure is disposed on the other side of the box-shaped beam module and is arranged along the length direction of the box-shaped beam module, and is attached to the box-shaped beam module. The wing skin covers the outer surfaces of the first side support structure and the second side support structure.

2. The aircraft propeller blade of claim 1, wherein, The box-shaped beam module includes an upper beam and a lower beam disposed below the upper beam and attached to the upper beam; The first side support structure is located on the left side of both the upper beam and the lower beam, and is attached to both; the second side support structure is located on the right side of both, and is attached to both.

3. The propeller blade of claim 2, wherein, A groove is provided on the lower beam or between the lower beam and the upper beam, near the root of the propeller blade, and a counterweight is provided in the groove.

4. The aircraft propeller blade of claim 1, wherein, Both the first side support structure and the second side support structure are hollow.

5. The aircraft propeller blade of claim 2, wherein, The wing skin includes an upper skin and a lower skin. The lower skin covers the area below the first side support structure and the second side support structure, and the upper skin covers the area above the first side support structure and the second side support structure.

6. The aircraft propeller blade of claim 5, wherein, One or more of the upper beam, the lower beam, the upper skin, and the lower skin are formed by carbon fiber 3D printing.

7. The aircraft propeller blade of claim 1, wherein, A metal blade holder is provided at the root of the propeller blade, and the metal blade holder is cylindrical.

8. The aircraft propeller blade of claim 1, wherein, The propeller blade has a protrusion at one end near the root of the propeller, and the cross-sectional area of ​​the box-shaped beam module, the first side support structure, and the second side support structure gradually decreases from the protrusion toward the end away from the root of the propeller.

9. The aircraft propeller blade of claim 1, wherein, The box-shaped beam module, the first side support structure, the second side support structure, and the wing skin are integrally formed by reaction injection molding of polyurethane material.

10. An aircraft characterized by, It includes several propeller blades as described in any one of claims 1-9.

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