A composite flexible propeller hub for aircraft propeller and propeller using the same

Abstract

The present invention discloses a composite material flexible hub for aircraft propellers and a propeller using the same. The flexible hub includes a first butterfly-shaped connector, an outer hub body, and an inner support bone, wherein: the outer side wall of the first butterfly-shaped connector is provided with a first butterfly-shaped annular groove; the inner support bone is sleeved outside the first butterfly connector, and the inner side surface of the inner support bone matches the first annular groove; the inner support bone and the first annular connector are mounted on the outer hub body; the outer hub body is provided with a connecting hole; the inner support bone has an outer extension rod extending out of the connecting hole, and the outer extension rod extends radially outward from the inner support bone. In the present invention, the composite material flexible hub for aircraft propellers and the propeller using the same have the technical effects of simple structure, high reliability, low cost, and long service life. The structure of the flexible hub improves the centrifugal tensile strength of the hub while reducing torsional resistance.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft propellers, in particular to an aircraft propeller composite material flexible hub and a propeller using the same. Background Art

[0002] The propeller hub is a key component with complex stresses, and its complexity brings problems with the structural strength, weight, reliability, etc. of the hub itself.

[0003] Currently, traditional metal propeller hubs on the market have problems such as heavy weight, complex structure, and difficulty in achieving pitch change.

[0004] How to design a high-strength, low-weight, and structurally reliable propeller hub has become a technical problem that needs to be urgently solved by technicians in the industry.

[0005] Moreover, the existing propeller hub is connected to the blade by a swing arm hinge, a straightening hinge and a pitch-changing hinge, and the blade angle of the blade is adjusted individually. As the Chinese patent application publication number CN110702355A discloses a device for adjusting the blade angle of a single blade, the disadvantage of this patent is that it is often necessary to adjust the blade angle individually when adjusting the blade angle, and multiple adjustments are required to ensure that the blade angles of multiple blades are equal. Summary of the Invention

[0006] In order to solve the technical problems existing in the background technology, the present invention proposes a composite material flexible hub for an aircraft propeller.

[0007] The present invention provides a composite flexible propeller hub for an aircraft propeller. The flexible propeller hub is made of a non-metallic material and includes a first butterfly-shaped connector, an outer propeller hub body, and an inner support bone, wherein:

[0008] A first butterfly-shaped annular groove is formed on the outer side wall of the first butterfly-shaped connector, and the depth of the first annular groove gradually increases from one end of the first butterfly-shaped connector to the other end of the first butterfly-shaped connector and then gradually decreases;

[0009] The inner supporting bone is sleeved outside the first butterfly-shaped connector, and the inner side surface of the inner supporting bone matches the first annular groove;

[0010] The inner support bone and the first annular connector are mounted on the outer hub body. The outer hub body is provided with a connection hole. The inner support bone has an outer extension rod extending out of the connection hole. The outer extension rod extends radially outward from the inner support bone.

[0011] On the basis of the above technical solution, as a further optimized solution of the present invention, it also includes a second butterfly-shaped connector, the outer wall of the second butterfly connector is provided with a second butterfly-shaped annular groove, the end of the outer extension rod away from the first annular connector has a second annular connecting portion, the second annular connecting portion is sleeved on the outside of the second butterfly connector, and the inner side wall of the second annular connecting portion matches the second butterfly-shaped annular groove.

[0012] Based on any of the above technical solutions, as a further optimized solution of the present invention, the axis of the second butterfly-shaped annular groove is parallel to the axis of the first butterfly-shaped annular groove.

[0013] Based on any of the above technical solutions, as a further optimized solution of the present invention, the outer diameter of the second annular connecting portion is greater than the outer diameter of the outer extension rod.

[0014] A propeller, comprising the above-mentioned flexible hub, blades, connecting parts, and flapping arms, wherein:

[0015] The blades are mounted on the inner support bone and can rotate relative to the outer hub body;

[0016] The swing arm is slidably mounted on the outer hub body, and a connecting piece is mounted between the swing arm and the blade. The sliding swing arm drives the blade to rotate relative to the outer hub body through the connecting piece.

[0017] Under the action of external force, the swinging arm is driven to slide relative to the flexible hub, and then the blade is driven to rotate relative to the flexible hub through the connecting member to change the blade angle. Specifically, the connecting member can be connected to the swinging arm and the blade through a ball connection in the existing technology.

[0018] On the basis of any of the above technical solutions, as a further optimized solution of the present invention, the axis of rotation of the flapping arm relative to the outer hub body coincides with the axis of the outer hub body.

[0019] Based on any of the above technical solutions, as a further optimized solution of the present invention, there are at least two connecting members and at least two blades, at least two blades are distributed along the circumference of the outer hub body, and one connecting member connects one blade to the flapping arm.

[0020] On the basis of any of the above technical solutions, as a further optimized solution of the present invention, a connecting hole is opened on the outer hub body, and a connecting column is fixed on the outer side wall of one end where the blade is connected to the flexible hub, and the connecting column passes through the connecting hole and slides in the connecting hole, and the connecting column is connected to the connecting piece.

[0021] Based on any of the above technical solutions, as a further optimized solution of the present invention, it further includes a first fixing column, which is installed between the blade and the outer extension rod, and the first fixing column is parallel to the axis of the outer hub body.

[0022] In the present invention, the proposed aircraft propeller composite material flexible hub and the propeller using the same have the technical effects of simple structure, high reliability, low cost and long life. The structure of the flexible hub improves the centrifugal tensile strength of the hub while reducing torsional resistance.

[0023] Additional aspects and advantages of the present invention will be set forth in part in the description which follows and, in part, will be obvious from the description which follows, or may be learned by practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a schematic diagram of the flexible hub structure of the present invention;

[0025] Figure 2 This is a schematic diagram of the outer hub body structure of the present invention;

[0026] Figure 3 This is a schematic diagram of the internal supporting bone structure of the present invention;

[0027] Figure 4 This is a cross-sectional view of the internal supporting bone of the present invention;

[0028] Figure 5 This is a schematic diagram of the propeller structure of the present invention;

[0029] Figure 6 For the present invention Figure 5 Cross-sectional view;

[0030] In the figure: 1. blade; 2. swinging arm; 20. sliding part; 21. supporting part; 3. connecting part; 4. flexible hub; 40. outer hub body; 400. connecting part; 4000. mounting cavity; 4001. second sliding hole; 401. extension part; 4010. connecting hole; 4011. connecting hole; 41. inner supporting bone; 410. first annular connecting part; 411. outer extension rod; 412. second annular connecting part; 5. connecting column; 6. first butterfly-shaped connecting part; 60. first butterfly-shaped annular groove; 61. first sliding hole; 7. second butterfly-shaped connecting part; 70. second butterfly-shaped annular groove; 8. first fixing column; 9. second fixing hole. DETAILED DESCRIPTION

[0031] The following describes embodiments of the present invention in detail. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar symbols 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 only to explain the present invention, and are not to be construed as limiting the present invention.

[0032] It should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be understood as limiting the present invention.

[0033] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0034] In the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0035] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0036] like Figure 5-6The aircraft propeller shown includes a blade 1, a flapping arm 2, a connecting member 3, and a flexible hub 4, wherein:

[0037] like Figure 1-4 The flexible hub 4 includes an outer hub body 40 and an inner support bone 41, wherein:

[0038] like Figure 2 As shown, the outer hub body 40 has a connecting portion 400 and an extending portion 401. The extending portion 401 extends outward along the radial direction of the connecting portion 400. A connecting hole 4010 is formed on the extending portion 401. Specifically, the extending portion 401 and the connecting portion 400 can be integrally formed.

[0039] In order to facilitate the installation of the inner support bone 41, the outer hub body 40 can be fixed by heat melting or welding for the upper and lower structures;

[0040] The blade 1 is rotatably mounted in the connecting hole 4010, and the outer diameter of the connecting end of the blade 1 is equal to the aperture of the connecting hole 4010;

[0041] like Figure 1 Specifically, a connecting hole 4011 is formed on the outer wall of the extension portion 401 of the outer hub body 40. The connecting hole 4011 is connected to the connecting hole 4010. A connecting post 5 is fixed to the connecting end of the blade 1 along its radial direction. The connecting post 5 passes through the connecting hole 4011. When the blade 1 is rotated relative to the outer hub body to adjust the angle of the blade 1, the connecting post 5 slides in the connecting hole 4011. Specifically, the outer diameter of the connecting post 5 is smaller than the width of the connecting hole 4011.

[0042] Specifically, there are three blades 1 and three extension parts 401 . The three blades 1 are evenly distributed along the circumference of the outer hub body 40 , and one blade 1 is installed in a connecting hole 4010 of one extension part 401 .

[0043] The connecting portion 400 of the outer hub body 40 has a mounting cavity 4000, and the inner support bone 41 is fixed in the mounting cavity 4000;

[0044] like Figure 3-4 As shown, specifically, the inner support bone 41 includes a first annular connecting portion 410 and an outer extension rod 411. The first annular connecting portion 410 is installed in the connecting portion 400. The outer extension rod 411 is installed on the first annular connecting portion 410 and extends outward along the radial direction of the first annular connecting portion 410 and extends into the connecting hole 4010. The first annular connecting portion 410 is coaxial with the outer hub body 40. The outer extension rod 411 is connected to one blade 1. Three outer extension rods 411 are provided and are evenly distributed along the circumference of the first annular connecting portion 410.

[0045] like Figure 6As shown, preferably, it also includes a first butterfly connector 6, the first butterfly connector 6 is fixed in the mounting cavity 4000 of the outer hub body 40, and the outer side wall of the first butterfly connector 6 is provided with a first butterfly annular groove 60, the cross section of the first butterfly annular groove 60 along its axial direction is arc-shaped, and the groove depth of the first butterfly annular groove 60 gradually increases from one end of the first butterfly connector 6 to the other end of the first butterfly connector 6 and then gradually decreases, and the first butterfly annular groove 60 is an arc surface, the first butterfly annular groove 60 is symmetrical with respect to the middle cross section of the first butterfly connector 6 (that is, along the cross section perpendicular to the axis of the first butterfly connector 6), the first annular connecting portion 410 is sleeved outside the first butterfly annular groove 60, and the inner side wall of the first annular connecting portion 410 matches the first butterfly annular groove 60;

[0046] like Figure 6 As shown, preferably, the outer side surface of the first annular connecting portion 410 is an arc surface that bulges toward a side away from the axis of the first annular connecting portion 410 . Specifically, the arc surface is symmetrical with the first butterfly ring groove 60 .

[0047] like Figure 6 As shown, the end of the outer extension rod 411 away from the first butterfly-shaped connector 6 has a second annular connecting portion 412, and the connecting end of the blade 1 has a connecting cavity. The outer side of the second annular connecting portion 412 is sleeved with the second butterfly-shaped connector 7. The second annular connector 3, the second butterfly connector 7 and part of the outer extension rod 411 are installed in the connecting cavity.

[0048] The axis of the second butterfly connector 7 is parallel to the axis of the outer hub body 40, and a second butterfly annular groove 70 is formed on the second butterfly connector 7, and the groove depth of the butterfly annular groove gradually increases from one end of the second butterfly connector 7 to the other end of the second butterfly connector 7 (from top to bottom in the figure) and then gradually decreases, and the second butterfly annular groove 70 is an arc surface, and the second butterfly annular groove 70 is symmetrical with respect to the middle cross section of the second butterfly connector 7 (that is, along the cross section perpendicular to the axis of the second butterfly connector 7), the second annular connecting portion 412 is sleeved on the second butterfly connector 7, and the inner side wall of the second annular connecting portion 412 matches the second butterfly annular groove 70, the outer extension rod 411 can be integrally formed with the second annular connecting portion 412, the outer diameter of the second annular connecting portion 412 is larger than the outer diameter of the outer extension rod 411, and the axis of the second annular connecting portion 412 is perpendicular to the axis of the outer extension rod 411;

[0049] Preferably, the outer diameter of the second annular connecting portion 412 of the outer extension rod 411 is an outwardly convex arc surface, and preferably, the arc surface is symmetrical with the second butterfly ring groove 70;

[0050] like Figure 5-6As shown, the blade 1 is further provided with a first fixing post 8, which connects the blade 1 to the second butterfly-shaped connector 7 of the outer extension rod 411. Specifically, a coaxial second fixing hole 9 is formed on the second butterfly-shaped connector 7 and the blade 1. The first fixing post 8 passes through the second fixing hole 9. The axis of the first fixing post 8 is perpendicular to the axis of the connecting end of the blade 1 and parallel to the axial direction of the outer hub body 40.

[0051] The swing arm 2 includes a sliding portion 20 and a supporting portion 21. The supporting portion 21 is fixed to the sliding portion 20. The sliding portion 20 is slidably mounted on the outer hub body 40 and penetrates the outer hub body 40. The outer support portion 21 is annular, and the sliding portion 20 is cylindrical. One end of the connecting member 3 is mounted on the supporting portion 21, and the other end of the connecting member 3 is mounted on the connecting column 5 of the blade 1. There are three connecting members 3, which are evenly distributed along the circumference of the support portion 21. One connecting member 3 is mounted on the connecting column 5 of one blade 1.

[0052] Specifically, a first sliding hole 61 is formed on the first butterfly-shaped connector 6 of the inner support bone 41 and is coaxial therewith. A second sliding hole 4001 is formed on the outer hub body 40. The second sliding hole 4001 is communicated with the mounting cavity 4000 and is coaxial with the first sliding hole 61. The sliding portion 20 passes through the first sliding hole 61 and the second sliding hole 4001 and slides within the coaxial first sliding hole 61 and the second sliding hole 4001.

[0053] The telescopic member on the aircraft that can drive the sliding part 20 to slide along the axis direction of the first sliding hole 61 and the second sliding hole 4001 is connected to the sliding part 20 and then drives the swinging arm 2 to slide relative to the outer hub body 40 to adjust the blade 1 angle.

[0054] During the working process of this embodiment: the sliding swinging arm 2 slides in a square along the axis of the propeller, the swinging arm 2 drives the connecting part 3 to slide, and the connecting part 3 drives the blade 1 to rotate relative to the outer hub body 40 through the connecting column 5. In the process of the blade 1 rotating relative to the outer hub body 40, the structure of the first butterfly ring groove 60 and the first annular connecting part 410 of the flexible hub 4 improves the centrifugal tensile strength of the hub while reducing the torsional resistance, and the mechanism of the second annular connecting part 412 and the second butterfly ring groove 70 further improves the centrifugal tensile strength of the hub while reducing the torsional resistance; at the same time, the blade 1 angles of the three blades 1 are adjusted at the same time by the swinging arm 2, which has a simple structure, high reliability, low cost and long service life.

[0055] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution and inventive concept of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. A composite flexible propeller hub for an aircraft, characterized in that: It comprises a first butterfly-shaped connecting member (6), an outer hub body (40) and an inner support bone (41), wherein: A first butterfly-shaped annular groove (60) is formed on the outer side wall of the first butterfly-shaped connector (6), and the depth of the first butterfly-shaped annular groove (60) gradually increases from one end of the first butterfly-shaped connector (6) to the other end of the first butterfly-shaped connector (6) and then gradually decreases; The inner supporting bone (41) is sleeved outside the first butterfly-shaped connecting piece (6), and the inner side surface of the inner supporting bone (41) matches the first butterfly-shaped annular groove (60); The inner support bone (41) and the first annular connecting member (3) are mounted on the outer hub body (40); the outer hub body (40) is provided with a connecting hole (4010); the inner support bone (41) has an outer extension rod (411) extending out of the connecting hole (4010); the outer extension rod (411) extends outward in a radial direction of the inner support bone (41); The invention also includes a second butterfly-shaped connecting member (7), the outer side wall of the second butterfly-shaped connecting member (7) is provided with a second butterfly-shaped annular groove (70), the end of the outer extension rod (411) away from the first annular connecting member (3) is provided with a second annular connecting portion (412), the second annular connecting portion (412) is sleeved outside the second butterfly-shaped connecting member (7), and the inner side wall of the second annular connecting portion (412) matches the second butterfly-shaped annular groove (70).

2. The aircraft propeller composite flexible hub according to claim 1, characterized in that: The axis of the second butterfly-shaped annular groove (70) is parallel to the axis of the first butterfly-shaped annular groove (60).

3. The aircraft propeller composite flexible hub according to claim 1, characterized in that: The outer diameter of the second annular connecting portion (412) is greater than the outer diameter of the outer extension rod (411).

4. A propeller, characterized in that: The invention comprises a flexible propeller hub (4) according to any one of claims 1 to 3, a propeller blade (1), a connecting member (3), and a swinging arm (2), wherein: The blade (1) is mounted on the inner support bone (41) and the blade (1) is rotatable relative to the outer hub body (40); The swinging arm (2) is slidably mounted on the outer hub body (40), and the connecting piece (3) is mounted between the swinging arm (2) and the blade (1). The sliding swinging arm (2) drives the blade (1) to rotate relative to the outer hub body (40) through the connecting piece (3).

5. The aircraft propeller composite flexible hub according to claim 4, characterized in that: The axis of rotation of the swinging arm (2) relative to the outer propeller hub body (40) coincides with the axis of the outer propeller hub body (40).

6. The aircraft propeller composite flexible hub according to claim 4, characterized in that: At least two of the connecting members (3) and the blades (1) are provided, at least two of the blades (1) are distributed along the circumference of the outer hub body (40), and one connecting member (3) connects one blade (1) and the flapping arm (2).

7. The aircraft propeller composite flexible hub according to claim 4, characterized in that: A connecting hole (4011) is provided on the outer hub body (40), and a connecting column (5) is fixed to the outer side wall of one end where the blade (1) is connected to the flexible hub (4), and the connecting column (5) passes through the connecting hole (4011) and slides in the connecting hole (4011), and the connecting column (5) is connected to the connecting member (3).

8. The aircraft propeller composite flexible hub according to claim 4, characterized in that: It also includes a first fixing column (8), which is installed between the blade (1) and the outer extension rod (411), and the first fixing column (8) is parallel to the axis of the outer hub body (40).

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