An aero gear with varying web thickness

Abstract

The present application belongs to the technical field of gear, and proposes an aviation gear with variable web thickness, comprising a shaft part, a tooth part and a web part, the first web part of the web part has a thickness smaller than that of the inner ring body part, the thickness of the connection between the first web part and the second web part is smaller than that of the connection between the second web part and the third web part, and the thickness of the connection between the third web part and the second web part is greater than that of the connection between the third web part and the supporting ring body part; the thickness of the connection between the second web part and the first web part and the thickness of the connection between the second web part and the third web part are both smaller than the thickness of the second web part at the radial middle position. The aviation gear with variable web thickness of the present application has a groove on the upper surface of the web part, thereby reducing the weight of the gear, adjusting and limiting the thickness of the first web part, the second web part and the third web part, and thereby regulating the overall torsional stiffness of the gear, the vibration characteristics of the gear and the bending strength.

Description

Technical Field

[0001] This invention belongs to the field of gear technology, and specifically relates to an aircraft gear with varying spoke thickness. Background Technology

[0002] Gear transmission has advantages such as high transmission efficiency, strong load-bearing capacity, long service life and compact structure. Therefore, it is widely used in the power transmission system of aero-engines. Aero-engine gears often operate under high speed and high load conditions, which leads to greater stress, more severe deformation and vibration during the service process. Therefore, there are extremely high requirements for the transmission performance of gears. The structure of the gears needs to be optimized to meet the requirements of strength and transmission characteristics, and to achieve the weight reduction of gears.

[0003] Therefore, many researchers have devoted themselves to the study of gear topology optimization methods to make up for the shortcomings of existing designs. On the one hand, traditional gear optimization methods rely on experience to drill holes and cut grooves in the spoke structure, which is costly and inefficient. Alternatively, finite element models can be used to perform topology optimization on the spoke structure based on variable density methods, particle swarm optimization algorithms, etc., to improve optimization efficiency. On the other hand, using existing commercial software such as OptiStruct and Abaqus for optimization design can effectively reduce gear mass and achieve optimization goals, but traditional algorithms cannot fully explore the design potential of the spoke structure.

[0004] Meanwhile, the current variable thickness design is based on the variable density method, which achieves better weight reduction while meeting load requirements through reasonable design of structural thickness, and obtains a novel configuration with better load-bearing performance. However, it is lacking in the field of gear structure optimization.

[0005] Therefore, overcoming the shortcomings of the existing technology is an urgent problem to be solved in this technical field. Summary of the Invention

[0006] To address the aforementioned problems, this invention proposes an aerospace gear with varying spoke thickness, comprising: a shaft portion, a tooth portion, and a spoke portion. The shaft portion and the spoke portion are coaxially connected, and the tooth portion is coaxially connected to the outer ring sidewall of the spoke portion. The spoke portion includes an inner ring body portion, a first spoke portion, a second spoke portion, a third spoke portion, and a supporting ring body portion, which are sequentially nested in an inner and outer ring configuration. The thickness of the first spoke portion is less than the thickness of the inner ring portion. The thickness at the connection between the first spoke portion and the second spoke portion is less than the thickness at the connection between the second spoke portion and the third spoke portion. The thickness at the connection between the third spoke portion and the second spoke portion is greater than the thickness at the connection between the third spoke portion and the supporting ring portion. The outer ring sidewall of the supporting ring portion is coaxially sleeved with the tooth portion. The thickness at the connection between the second spoke and the first spoke, and the thickness at the connection between the second spoke and the third spoke, are both less than the thickness at the radial midpoint of the second spoke.

[0007] Furthermore, the spoke portion includes an inner ring sidewall, a lower surface, a first outer ring sidewall, a second outer ring sidewall, and an upper surface; The lower surface is the sidewall of the spoke portion facing the shaft portion. The lower surface is connected to one side of the first outer ring sidewall. The other side of the first outer ring sidewall is connected to one side of the second outer ring sidewall. The upper surface connects the other side of the second outer ring sidewall to one side of the inner ring sidewall. The lower surface is horizontally arranged, and the second outer ring sidewall forms a first angle with the lower surface.

[0008] Furthermore, the upper and lower surfaces of the first spoke are arranged horizontally.

[0009] Furthermore, the upper surface of the second spoke section adopts a curved structure.

[0010] Furthermore, the thickness of the third spoke gradually increases with the increase of the distance from the center line of the spoke portion.

[0011] Furthermore, the upper surface of the supporting ring portion includes a first surface and a second surface. One side of the first surface is connected to the sidewall of the second outer ring, and the other side of the second surface is connected to the upper surface of the third spoke portion. The second surface and the upper surface of the third spoke portion form a third angle.

[0012] Furthermore, the inner edge radius of the inner ring body is less than or equal to 12.20 mm and greater than or equal to 8.40 mm; The outer radius of the supporting ring body is less than or equal to 26.60 mm and greater than or equal to 33.90 mm; The width of the second outer ring sidewall is less than or equal to 8.60 mm, and the axial length of the inner ring body is greater than or equal to 5.00 mm and less than or equal to 7.40 mm.

[0013] Furthermore, the radius of the connection edge between the first surface and the second outer ring sidewall is the difference between the outer edge radius of the supporting ring body and 6.60 mm; The radius of the connecting edge between the first and second surfaces is the difference between the outer edge radius of the supporting ring and 7.30 mm; The radius of the connection between the lower surface and the first outer ring sidewall is the difference between 0.73 times the outer edge radius of the supporting ring body and 0.27 times the inner edge radius of the inner ring body.

[0014] Furthermore, the inner ring body includes a first ring and a second ring that are connected in an inner and outer manner. The upper surface of the first ring is horizontally arranged, and the upper surface of the second ring connects the upper surface of the first ring and the upper surface of the first spoke. The upper surface of the second ring and the upper surface of the first spoke form a second angle. The radius of the connecting edge between the upper surface of the first ring and the upper surface of the second ring is the sum of the inner edge radius of the inner ring body and 2.40 mm.

[0015] Furthermore, the radial thickness of the first spoke portion is 0.11 times the difference between the outer radius of the supporting ring portion and the inner radius of the inner ring portion; The radial thickness of the second spoke portion is 0.21 times the difference between the outer radius of the supporting ring portion and the inner radius of the inner ring portion; The radial thickness of the third spoke portion is 0.27 times the difference between the outer radius of the supporting ring portion and the inner radius of the inner ring portion.

[0016] Compared with the prior art, the embodiments of the present invention have at least the following advantages: The present invention relates to an aerospace gear with varying spoke thickness. Based on a traditional gear, grooves are formed on the upper surface of the spoke portion, thereby reducing the weight of the spoke portion and the gear as a whole. Based on the different functions of different positions of the spoke portion, the thickness of the first, second, and third spoke portions is adjusted and limited to control the overall torsional stiffness, vibration characteristics, and bending strength of the gear. This achieves overall weight reduction while meeting load-bearing requirements, thus optimizing the gear structure.

[0017] Other features and advantages of the invention will be set forth in the following description, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures pointed out in the description and the drawings. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 A schematic diagram of an aircraft gear with varying spoke thickness in an embodiment of the present invention is shown; Figure 2 A bottom view schematic diagram of an aircraft gear with varying spoke thickness in an embodiment of the present invention is shown; Figure 3 It shows Figure 2 Cross-sectional view of AA in the middle; Figure 4 A schematic diagram showing the equivalent stress calculation results of an aircraft gear with varying spoke thickness in an embodiment of the present invention is provided.

[0020] In the figure, shaft part 1, tooth part 2, spoke part 3, inner ring part 4, first spoke part 5, second spoke part 6, third spoke part 7, and supporting ring part 8. Detailed Implementation

[0021] The following description provides many different embodiments or examples for implementing various features of the invention. The elements and arrangements described in the specific examples below are only for concise expression of the invention and are merely examples, not intended to limit the invention.

[0022] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, 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.

[0023] This invention provides an aircraft gear with variable spoke thickness design. By significantly reducing gear mass and saving materials to lower costs when stress is much lower than the yield limit, this design achieves a high load-bearing capacity. Figure 1 A schematic diagram of an aircraft gear with varying spoke thickness in an embodiment of the present invention is shown. Figure 1 In the process, the aircraft gear with varying spoke thickness includes: a shaft portion 1, a tooth portion 2, and a spoke portion 3 in a circular ring structure, wherein the shaft portion 1 and the spoke portion 3 are coaxially connected, and the tooth portion 2 is coaxially connected to the outer ring sidewall of the spoke portion 3; It should be further explained that the axial thickness of traditional aircraft gear spokes is usually of a single specification, i.e., the axial thickness value is fixed. This invention creates grooves on the upper surface of the spoke portion 3, thereby reducing the weight of the spoke portion 3. Based on the different structures of the upper surface of the spoke portion 3, the spoke portion 3 is divided into an inner ring body 4, a first spoke portion 5, a second spoke portion 6, a third spoke portion 7, and a supporting ring body 8, which are sequentially nested together. Figure 3 In the example shown, the inner ring body 4, the first spoke 5, the second spoke 6, the third spoke 7, and the supporting ring body 8 are all divided by dashed lines; refer to Figure 2 The inner ring body 4 is a circular structure with the axis of the spoke part 3 as the axis. The side wall of the inner ring body 4 is coaxially connected to the shaft part 1 of the gear for torque transmission. The supporting ring body 8 is used to connect the tooth part 2 of the gear to achieve direct support for the root of the gear and withstand the bending stress generated by meshing. The thickness value is defined as the distance between the upper and lower surfaces of the spoke portion 3. The thickness design of the inner ring portion 4 is based on the thickness of the original spoke portion. The thickness of the first spoke portion 5 is less than the thickness of the inner ring portion 4. The thickness at the connection between the first spoke portion 5 and the second spoke portion 6 is less than the thickness at the connection between the second spoke portion 6 and the third spoke portion 7. The thickness at the connection between the third spoke portion 7 and the second spoke portion 6 is greater than the thickness at the connection between the third spoke portion 7 and the supporting ring portion 8. The outer ring sidewall of the supporting ring portion 8 is coaxially sleeved with the tooth portion 2. The thickness at the connection between the second spoke portion 6 and the first spoke portion 5, and the thickness at the connection between the second spoke portion 6 and the third spoke portion 7, are both less than the height of the radial center position of the second spoke portion 6.

[0024] The aviation gear with varying spoke thickness disclosed in this invention, based on the traditional gear, has grooves formed on the upper surface of the spoke portion 3, thereby reducing the weight of the spoke portion 3 and the gear as a whole. Based on the different functions of different positions of the spoke portion 3, the thickness of the first spoke portion 5, the second spoke portion 6, and the third spoke portion 7 are adjusted and limited to control the overall torsional stiffness, vibration characteristics, and bending strength of the gear. While meeting the load-bearing requirements, the overall weight is reduced, thus optimizing the gear structure.

[0025] In this embodiment, the spoke portion 3 includes an inner ring sidewall, a lower surface, a first outer ring sidewall, a second outer ring sidewall, and an upper surface; The lower surface is the sidewall of the spoke portion 3 facing the shaft portion 1. The lower surface is connected to one side of the first outer ring sidewall, and the other side of the first outer ring sidewall is connected to one side of the second outer ring sidewall. The upper surface connects the other side of the second outer ring sidewall to one side of the inner ring sidewall. The lower surface is horizontally arranged, and the second outer ring sidewall forms a first angle α with the lower surface. For example, the first angle α = 128.90°.

[0026] In this embodiment, the upper and lower surfaces of the first spoke portion 5 are arranged horizontally, and the thickness of the first spoke portion 5 is fixed. Through the parallel design of the upper and lower surfaces of the first spoke portion 5, the gear as a whole is provided with bending and torsional stiffness to resist the stress of shaft deformation.

[0027] In this embodiment, based on the fact that the thickness at the connection between the second spoke portion 6 and the first spoke portion 5 and the thickness at the connection between the second spoke portion 6 and the third spoke portion 7 are both less than the thickness at the radial midpoint of the second spoke portion 6, the upper surface of the second spoke portion 6 is further limited to adopt a curved structure, so that the cross section of the upper surface of the second spoke portion 6 changes with a curve, thereby adjusting the vibration characteristics of the gear and avoiding resonance damage.

[0028] For example, the upper surface cross section of the second spoke portion 6 is formed by fitting a quadratic function curve, and the highest point of the curve is located between the connection point of the second spoke portion 6 and the first spoke portion 5 and the third spoke portion 7.

[0029] The expression for the cross-sectional curve of the upper surface of the second spoke section 6 is as follows: (1) In the formula, x represents the coordinate direction, y represents the coordinate direction, and a, b, and c represent parameters.

[0030] In this embodiment, the thickness of the third spoke portion 7 gradually increases with the increase of the distance from the center line of the spoke portion 3, so that the cross-section of the upper surface of the third spoke portion 7 has a linear trend, which meets the bending strength requirements at the tooth root and prevents the tooth from breaking.

[0031] It should be further noted that the aviation gear based on the variable thickness design of the spokes proposed in this application is applicable when the tangential component of the meshing force on the gear teeth is less than or equal to 522N, the axial component of the meshing force on the gear teeth is less than or equal to 280N, and the gear speed is less than or equal to 350rpm.

[0032] The upper surface of the supporting ring part 8 includes a first surface and a second surface. One side of the first surface is connected to the second outer ring sidewall, and the other side of the second surface is connected to the upper surface of the third spoke part 7. The second surface and the upper surface of the third spoke part 7 form a third angle. For example, γ is the angle between the second surface and the upper surface of the third spoke part 7, and γ = 69.90°.

[0033] In this embodiment, the specifications of the inner ring body 4 and the supporting ring body 8 are used as independent variables. Correspondingly, the inner edge radius R0 of the inner ring body 4 is set to be less than or equal to 12.20 mm and greater than or equal to 8.40 mm. The outer radius R1 of the supporting ring part 8 is less than or equal to 26.60 mm and greater than or equal to 33.90 mm, specifically referring to the distance between the connecting edge of the first outer ring sidewall and the second outer ring sidewall and the center line of the spoke part 3. The width d1 of the second outer ring sidewall is less than or equal to 8.60 mm, and the axial length d2 of the inner ring body 4 is greater than or equal to 5.00 mm and less than or equal to 7.40 mm.

[0034] Correspondingly, the radius R2 of the connection between the first surface and the second outer ring sidewall is the difference between the outer edge radius R1 of the supporting ring body 8 and 6.60 mm; The radius R4 of the connecting edge between the first and second surfaces is the difference between the outer edge radius R1 of the supporting ring part 8 and 7.30 mm; The radius R3 of the connection between the lower surface and the first outer ring sidewall is the difference between 0.73 times the outer edge radius R1 of the supporting ring body 8 and 0.27 times the inner edge radius R0 of the inner ring body 4. Furthermore, the inner ring body 4 includes a first ring and a second ring that are connected in an inner and outer manner. The upper surface of the first ring is horizontally arranged, and the upper surface of the second ring connects the upper surface of the first ring and the upper surface of the first spoke portion 5. The upper surface of the second ring and the upper surface of the first spoke portion 5 form a second included angle β. For example, the second included angle β = 123.80°. Correspondingly, the connecting edge radius R5 of the upper surface of the first ring and the upper surface of the second ring is the sum of the inner edge radius R0 of the inner ring body 4 and 2.40 mm; In this embodiment, the upper surfaces of the inner ring body 4, the first spoke portion 5, the second spoke portion 6, the third spoke portion 7, and the supporting ring body 8 are all rounded. The rounded corner radius r1 between the upper surface of the second ring body and the upper surface of the first spoke portion 5, the rounded corner radius r2 between the upper surface of the first spoke portion 5 and the upper surface of the second spoke portion 6, and the rounded corner radius r3 between the upper surface of the second spoke portion 6 and the upper surface of the third spoke portion 7 are all consistent. Furthermore, the rounded corner radius r4 between the upper surface of the third spoke portion 7 and the second surface of the supporting ring body 8 is twice the rounded corner radius r3 between the upper surface of the second spoke portion 6 and the upper surface of the third spoke portion 7.

[0035] Correspondingly, the radial thickness L1 of the first spoke portion 5 is 0.11 times the difference between the outer edge radius R1 of the supporting ring portion 8 and the inner edge radius R0 of the inner ring portion 4; The radial thickness L2 of the second spoke portion 6 is 0.21 times the difference between the outer radius R1 of the supporting ring portion 8 and the inner radius R0 of the inner ring portion 4. The radial thickness L3 of the third spoke portion 7 is 0.27 times the difference between the outer radius R1 of the supporting ring portion 8 and the inner radius R0 of the inner ring portion 4.

[0036] In this embodiment, the height difference H1 between the connecting edge of the first surface of the supporting ring part 8 and the second outer ring sidewall and the lower surface is 11.40 mm; The height difference W between the connecting edge of the first and second surfaces of the supporting ring part 8 and the lower surface is 11.10 mm.

[0037] In this embodiment, the density of the material used to manufacture the aircraft gear with varying spoke thickness is less than or equal to 7860 kg / m³. 3 The yield strength of the material used to manufacture the bevel gear spokes is greater than or equal to 940 MPa.

[0038] Based on the inner edge radius R0 of the inner ring body 4 and the outer edge radius R1 of the supporting ring body 8, the following summary can be made: R0 represents the inner edge radius of the inner ring body 4, 8.40≤R0≤12.20, in mm; R1 represents the outer radius of the supporting ring part 8, 26.60≤R1≤33.90, in mm; R2 represents the radius of the connection between the first surface and the second outer ring sidewall, R2=R1-6.60, in mm; R3 represents the radius of the connection between the lower surface and the first outer ring sidewall, R3 = R1 - 0.27(R1 - R0), in mm; R4 represents the radius of the connecting edge between the first and second faces, R4 = R1 - 7.30, in mm; R5 represents the radius of the connecting edge between the upper surface of the first ring and the upper surface of the second ring. R5 = R0 + 2.40, and the unit is mm. H1 represents the height difference between the connecting edge of the first surface of the supporting ring part 8 and the second outer ring sidewall and the lower surface, H1 = 11.40, in mm; W represents the height difference between the connecting edge of the first and second surfaces of the supporting ring part 8 and the lower surface, W = 11.10, in mm; L1 represents the radial thickness of the first spoke portion 5, L1 = 0.11(R1 - R0), in mm; L2 represents the radial thickness of the second spoke portion 6, L2 = 0.21(R1-R0), in mm; L3 represents the radial thickness of the third spoke portion 7, L3 = 0.27(R1-R0), in mm; α represents the first angle between the second outer ring sidewall and the lower surface, α = 128.90°; β represents the second included angle between the upper surface of the second ring and the upper surface of the first spoke portion 5, β = 123.80°; γ represents the third included angle between the second surface and the upper surface of the third spoke portion 7, γ = 69.90°; r1 represents the fillet radius between the upper surface of the second ring and the upper surface of the first spoke 5, r1 = 0.50, in mm; r2 represents the fillet radius between the upper surface of the first spoke portion 5 and the upper surface of the second spoke portion 6, r2 = 0.50, in mm; r3 represents the fillet radius between the upper surface of the second spoke portion 6 and the upper surface of the third spoke portion 7, r3 = 0.50, in mm; r4 represents the fillet radius between the upper surface of the third spoke portion 7 and the second surface of the supporting ring portion 8, r4=1, and the unit is mm.

[0039] For further explanation of this application, see references. Figure 1 and Figure 3 With a material density of 7.86 g / cm³ 3 Taking 9310 steel as an example, the corresponding material yield strength is greater than or equal to 940MPa. Taking the input load as the maximum, and based on the inner edge radius R0 of the inner ring body 4 being 9.50mm, the outer edge radius R1 of the support body 4 being 30.82mm, the width d1 of the second outer ring sidewall being 8.07mm, and the axial length d2 of the inner ring body 4 being 5.60mm, the parameters of each structure are summarized and described as follows: R0 represents the inner edge radius of the inner ring body 4, R0 = 9.50 mm; R1 represents the outer radius of the supporting ring part 8, R1 = 30.82 mm; R2 represents the radius of the connection between the first surface and the second outer ring sidewall, R2 = 24.22 mm; R3 represents the radius of the connection between the lower surface and the first outer ring sidewall, R3 = 24.97 mm; R4 represents the radius of the connecting edge between the first and second surfaces, R4 = 23.49 mm; R5 represents the radius of the connecting edge between the upper surfaces of the first ring and the upper surfaces of the second ring, R5 = 11.86 mm; H1 represents the height difference between the connecting edge of the first surface of the supporting ring part 8 and the second outer ring sidewall and the lower surface, H1 = 11.40 mm; W represents the height difference between the connecting edge of the first and second surfaces of the supporting ring part 8 and the lower surface, W = 11.10 mm; L1 represents the radial thickness of the first spoke portion 5, L1 = 2.24 mm; L2 represents the radial thickness of the second spoke portion 6, L2 = 4.10 mm; L3 represents the radial thickness of the third spoke portion 7, L3 = 5.24 mm; α represents the angle between the bottom surface of the spoke and the bottom surface of the tooth (2), α = 128.90°; β represents the angle between the first line segment (A1) and the second line segment (A2), β = 123.80°; γ represents the angle between the fourth line segment (A4) and the fifth line segment (A5), γ = 69.90°; r1 represents the fillet radius between the upper surface of the second ring and the upper surface of the first spoke portion 5, r1 = 0.50 mm; r2 represents the fillet radius between the upper surface of the first spoke portion 5 and the upper surface of the second spoke portion 6, r2 = 0.50 mm; r3 represents the fillet radius between the upper surface of the second spoke portion 6 and the upper surface of the third spoke portion 7, r3 = 0.50 mm; r4 represents the fillet radius between the upper surface of the third spoke portion 7 and the second surface of the supporting ring portion 8, r4=1mm; d1 represents the width of the second outer ring sidewall, d1 = 8.07 mm; d2 represents the axial length of the inner ring body 4, d2=5.60mm.

[0040] The thickness variation curve of the second spoke section 6 was fitted as follows: (2) In the formula, x represents the coordinate direction, y represents the coordinate direction, and a, b, and c represent parameters. The formula takes the point on the upper surface where the thickness of the second spoke part 6 is the maximum as the origin.

[0041] Finite element simulation analysis was performed on an aerospace gear with varying spoke thickness designed based on the above parameters. The mesh element size was adjusted to 2 mm, and the number of mesh elements was 26775. The calculated equivalent stress (von Mises stress) contour plot is shown below. Figure 4 As shown, its volume is 2.6146 × 10⁻⁶. 4 mm 3 The mass is 0.2055 kg.

[0042] Analysis showed that the maximum von Mises stress of the gear under different working conditions was 348.36 MPa, which is much less than the yield strength, and the mass was reduced by 24.9%. This achieved a significant reduction in the overall weight of the gear while meeting the yield limit requirements, thus improving the overall performance of the equipment, saving materials, and reducing costs.

[0043] In the description of this invention, 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 indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly; for example, they may refer to a fixed connection, a detachable connection, or an integral connection; they may refer to a mechanical connection, an electrical connection, or a connection that allows for communication; they may refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this invention according to the specific circumstances.

[0044] It should be understood that all terms used to indicate orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing the present invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and should not be construed as a limitation of the present invention.

[0045] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An aircraft gear with varying spoke thickness, comprising: Shaft (1), toothed part (2), and spoke part (3), wherein the shaft (1) and the spoke part (3) are coaxially connected, and the toothed part (2) and the outer ring sidewall of the spoke part (3) are coaxially connected. The spoke part (3) is characterized in that the spoke part (3) includes an inner ring body part (4), a first spoke part (5), a second spoke part (6), a third spoke part (7), and a supporting ring body part (8) that are sequentially nested in an inner and outer ring. The thickness of the first spoke portion (5) is less than the thickness of the inner ring portion (4), the thickness of the connection between the first spoke portion (5) and the second spoke portion (6) is less than the thickness of the connection between the second spoke portion (6) and the third spoke portion (7), and the thickness of the connection between the third spoke portion (7) and the second spoke portion (6) is greater than the thickness of the connection between the third spoke portion (7) and the supporting ring portion (8). The outer ring sidewall of the supporting ring portion (8) is coaxially sleeved with the tooth portion (2). The thickness at the connection between the second spoke portion (6) and the first spoke portion (5), and the thickness at the connection between the second spoke portion (6) and the third spoke portion (7) are both less than the thickness at the radial center of the second spoke portion (6); The spoke portion (3) includes an upper surface and a lower surface, and the upper surface and the lower surface of the first spoke portion (5) are arranged horizontally; The upper surface of the second spoke portion (6) adopts a curved structure; The thickness of the third spoke portion (7) gradually increases with the increase of the distance from the center line of the spoke portion (3); The inner ring body (4) includes a first ring and a second ring that are connected in an inner and outer manner. The upper surface of the first ring is arranged horizontally, and the upper surface of the second ring connects the upper surface of the first ring and the upper surface of the first spoke (5). The upper surface of the second ring and the upper surface of the first spoke (5) form a second angle.

2. The aircraft gear with varying spoke thickness according to claim 1, characterized in that, The spoke portion (3) includes an inner ring sidewall, a first outer ring sidewall, and a second outer ring sidewall; The lower surface is the sidewall of the spoke portion (3) facing the shaft portion (1), the lower surface is connected to one side of the first outer ring sidewall, the other side of the first outer ring sidewall is connected to one side of the second outer ring sidewall, and the upper surface connects the other side of the second outer ring sidewall to one side of the inner ring sidewall. The lower surface is horizontally arranged, and the second outer ring sidewall forms a first angle with the lower surface.

3. The aircraft gear with varying spoke thickness according to claim 2, characterized in that, The upper surface of the supporting ring part (8) includes a first surface and a second surface. One side of the first surface is connected to the second outer ring sidewall, and the other side of the first surface is connected to the upper surface of the third spoke part (7). The second surface and the upper surface of the third spoke part (7) form a third angle.

4. The aircraft gear with varying spoke thickness according to claim 3, characterized in that, The inner edge radius of the inner ring body (4) is less than or equal to 12.20 mm and greater than or equal to 8.40 mm; The outer radius of the supporting ring part (8) is less than or equal to 26.60 mm and greater than or equal to 33.90 mm; The width of the second outer ring sidewall is less than or equal to 8.60 mm, and the axial length of the inner ring body (4) is greater than or equal to 5.00 mm and less than or equal to 7.40 mm.

5. The aircraft gear with varying spoke thickness according to claim 4, characterized in that, The radius of the connection between the first surface and the second outer ring sidewall is the difference between the outer edge radius of the supporting ring body (8) and 6.60 mm; The radius of the connecting edge between the first and second surfaces is the difference between the outer edge radius of the supporting ring part (8) and 7.30 mm; The radius of the connection between the lower surface and the first outer ring sidewall is the difference between 0.73 times the outer edge radius of the supporting ring body (8) and 0.27 times the inner edge radius of the inner ring body (4).

6. The aircraft gear with varying spoke thickness according to claim 5, characterized in that, The radius of the connecting edge between the upper surface of the first ring and the upper surface of the second ring is the sum of the inner edge radius of the inner ring body (4) and 2.40 mm.

7. The aircraft gear with varying spoke thickness according to claim 6, characterized in that, The radial thickness of the first spoke portion (5) is 0.11 times the difference between the outer radius of the supporting ring portion (8) and the inner radius of the inner ring portion (4); The radial thickness of the second spoke portion (6) is 0.21 times the difference between the outer radius of the supporting ring portion (8) and the inner radius of the inner ring portion (4); The radial thickness of the third spoke portion (7) is 0.27 times the difference between the outer radius of the supporting ring portion (8) and the inner radius of the inner ring portion (4).

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