Pressure-bearing cup assembly for aviation aircraft wheel and design method of pressure-bearing cup assembly

Abstract

The invention relates to the technical field of aviation brake aircraft wheels, in particular to a pressure-bearing cup assembly for an aviation aircraft wheel and a design method thereof.The design method comprises the steps that the maximum pressure stress of the pressure-bearing cup assembly when the pressure stress requirement is met is obtained; obtaining the shear stress of the pressure-bearing cup assembly when the shear stress requirement is met; acquiring the thickness and the diameter of the disc body when the strength requirement of the dangerous area is met; and designing a pressure-bearing cup assembly. The working stability and reliability of the pressure-bearing cup assembly can be guaranteed in the design stage, and the problems that the production cost is increased and the period is increased due to pressure-bearing cup design defects caused by lack of theoretical support are solved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft brake wheels, and in particular to a pressure cup assembly for an aircraft wheel and a design method thereof. Background Art

[0002] The wheel pressure cup is a critical load-bearing component of aircraft brakes, and its strength is directly related to the reliability of the aircraft's braking system. The pressure cup is fixed to the pressure plate with rivets, providing support during operation and subject to pressure from both the plate and the brake housing. Due to its structural characteristics, the pressure cup contains regions within it that are simultaneously subjected to compressive and shear stresses. Yielding is the primary mode of failure, and failure of the pressure cup can lead to reduced braking efficiency or even failure.

[0003] In the current brake device design, the design of the pressure cup still mainly relies on the designer's experience, and its strength verification usually relies on destructive testing. If it is found after verification that the design strength of the pressure cup is insufficient, a series of related components such as the pressure cup and pressure plate need to be redesigned and tested, which increases the product design cycle.

[0004] Therefore, it is necessary to provide a pressure cup assembly for an aircraft wheel and a design method thereof to solve the above problems. Summary of the Invention

[0005] In order to solve the problems of lack of theoretical analysis and insufficient reliance on experience in the pressure cup design process in the prior art, the present invention provides a pressure cup assembly for an aircraft wheel and a design method thereof, so as to ensure its working stability and reliability during the design stage and reduce the production cost and cycle increase losses caused by pressure cup design defects due to lack of theoretical support.

[0006] The present invention provides a pressure cup assembly for an aircraft wheel, which adopts the following technical solutions, including: a disc body, on which a pressure-bearing portion is provided; The disc body is used to connect with the pressure disc, and the pressure-bearing part is used to be fixed radially with the brake housing.

[0007] Preferably, the disc body is provided with rivet holes for inserting rivets, and the rivets are used to connect the disc body and the pressure disc.

[0008] Preferably, the pressure-bearing part is an arc-shaped support block, which is arranged in the middle of the disc body. The side of the arc-shaped support block facing away from the disc body is an arc-shaped surface. A pin hole for passing a pin is provided on the arc-shaped surface of the arc-shaped support block, and the pin is used to connect the arc-shaped support block and the brake housing.

[0009] Preferably, weight-reducing grooves are provided on the disc bodies on both sides of the arc-shaped support block, wherein the rivet hole is provided in one of the weight-reducing grooves.

[0010] A design method for a pressure cup assembly for an aircraft wheel adopts the following technical solutions, including: Obtain the load on a single pressure cup assembly based on the total pressure when the brake device is working; Obtain the maximum compressive stress of the pressure cup assembly based on the force-bearing area of the disc body, the force-bearing area of the pressure-bearing part, and the load on the pressure cup assembly; When the maximum compressive stress meets the compressive stress requirement, the compressive strength of the pressure cup assembly is qualified. If not, the diameter of the disc body is adjusted until the adjusted maximum compressive stress meets the compressive stress requirement, and the target maximum compressive stress when the compressive stress requirement is met is obtained. Obtaining the shear stress of the pressure cup assembly according to the shear area of the pressure cup assembly, the force-bearing area of the disk of the pressure cup assembly, the force-bearing area of the pressure-bearing part, and the load on the pressure cup assembly; When the shear stress meets the shear stress requirement, the shear strength of the pressure cup assembly is qualified. If not, the thickness of the disc body is adjusted until the adjusted shear stress meets the shear stress requirement, and the target shear stress when the shear stress requirement is met is obtained. According to the target maximum compressive stress and target shear stress, the principal stress at the root of the pressure-bearing part is obtained, and the equivalent stress is obtained according to the principal stress and the fourth strength theory. If the equivalent stress meets the strength requirement of the hazardous area, the strength of the root of the pressure-bearing part of the pressure cup assembly meets the requirement. If the equivalent stress meets the strength requirement of the hazardous area, the thickness and diameter of the disk body are adjusted at the same time until the adjusted equivalent stress meets the strength requirement of the hazardous area. Design the pressure cup assembly based on the disc thickness and disc diameter when the equivalent stress meets the strength requirements of the hazardous area.

[0011] Preferably, the step of obtaining the force-bearing area of the disc is: The force-bearing area of the disk of the pressure cup assembly is obtained according to the disk diameter of the pressure cup assembly, the diameter and number of the rivet holes, and the diameter of the pin holes.

[0012] Preferably, the step of obtaining the force-bearing area of the pressure-bearing part is: The force-bearing area of the pressure-bearing part is obtained according to the bearing width of the pressure-bearing part, the thickness of the pressure-bearing part and the diameter of the pin hole.

[0013] Preferably, the step of obtaining the maximum compressive stress of the pressure cup assembly is: Obtain the stress of the disc body according to the force-bearing area of the disc body and the load on the pressure cup assembly; Obtaining the stress of the pressure-bearing part according to the force-bearing area of the pressure-bearing part and the load on the pressure cup assembly; The maximum compressive stress among the stress of the disk body and the stress of the pressure-bearing part is taken as the maximum compressive stress of the pressure-bearing cup assembly.

[0014] Preferably, the step of obtaining the shear area of the pressure cup assembly is: The shear area of the shear stress on the pressure cup is obtained according to the load-bearing width of the arc surface of the pressure-bearing part, the thickness of the pressure-bearing part and the thickness of the disc body.

[0015] Preferably, the step of obtaining the principal stress at the root of the pressure-bearing part according to the maximum compressive stress that meets the compressive stress requirement and the shear stress that meets the shear stress requirement is: According to the maximum compressive stress that meets the compressive stress requirements and the shear stress that meets the shear stress requirements, a biaxial stress state matrix of the root of the pressure-bearing part is constructed; The principal stress at the root of the pressure-bearing part is obtained by calculating the characteristic value of the biaxial stress state matrix.

[0016] The beneficial effects of the present invention are: By judging the compressive strength and shear strength of the pressure cup assembly and adjusting the disk diameter and disk thickness of the pressure cup assembly accordingly to ensure that the compressive strength and shear strength of the pressure cup assembly are qualified, a comprehensive analysis is conducted on the compressive stress and shear stress on the root of the pressure-bearing part, and the disk thickness and disk diameter are adjusted at the same time to ensure that the strength of the dangerous area (root of the pressure-bearing part) of the pressure cup assembly meets the requirements. That is, by using the design method of the present invention, the stability and reliability of the pressure cup assembly can be guaranteed during the design stage, reducing the problems of increased production costs and cycles caused by pressure cup design defects due to lack of theoretical support. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0018] Figure 1 This is a schematic structural diagram of a pressure cup assembly for an aircraft wheel according to the present invention; Figure 2 A top view and a cross-sectional view of a pressure cup assembly for an aircraft wheel according to the present invention; Figure 3 This is a schematic diagram of the installation of a pressure cup assembly for an aircraft wheel in a brake assembly according to the present invention; Figure 4 This is a load distribution diagram of a pressure cup assembly for an aircraft wheel according to the present invention; Figure 5 A simplified diagram of a stress calculation model for a pressure cup assembly in an embodiment of the present invention; Figure 6Flowchart of a design method for a pressure cup assembly in an embodiment of the present invention.

[0019] In the figure: 1, pressure plate; 2, pressure cup assembly; 21, plate body; 22, pressure-bearing part; 211, rivet hole; 221, pin hole; 3, pin; 4, rivet. DETAILED DESCRIPTION

[0020] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0021] An embodiment of a pressure cup assembly for an aircraft wheel of the present invention is as follows Figure 1 As shown, it includes: a disc body 21, and a pressure-bearing portion 22 is provided on the disc body 21; wherein the disc body 21 is used to connect with the pressure disc 1, and the pressure-bearing portion 22 is used to be fixed radially with the brake housing. For example, in a specific embodiment, as Figure 1 and Figure 2 As shown, the disc body 21 is provided with a rivet hole 211 for inserting a rivet 4, which is used to connect the disc body 21 and the pressure plate 1. The pressure-bearing portion 22 is an arc-shaped support block, which is located in the middle of the disc body 21. The side of the arc-shaped support block facing away from the disc body 21 is an arc-shaped surface. The arc-shaped surface of the arc-shaped support block is provided with a pin hole 221 for inserting a pin, which is used to connect the arc-shaped support block to the brake housing. The disc body 21 has weight-reducing grooves on both sides of the arc-shaped support block, and the rivet hole 211 is located in one of the weight-reducing grooves.

[0022] like Figure 3 As shown, when the pressure cup assembly 2 is installed, the disk body 21 of the pressure cup assembly 2 is connected to the disk body 21 and the pressure plate 1 through the rivet 4, the pin 3 is passed through the pin hole 221 of the arc-shaped support block, and the end thereof after passing through the pin hole 221 is connected to the brake housing.

[0023] An embodiment of a design method for a pressure cup assembly for an aircraft wheel is described. In this embodiment, the diameter and thickness of the pressure cup assembly's disc are used as design variables for verification. This embodiment uses titanium alloy material, grade TC11, with a yield strength of 910 MPa, to meet the requirements of the "GJB 2218A-2008 Specification for Titanium and Titanium Alloy Bars and Forgings for Aviation" standard. With a safety factor of 3, the allowable tensile stress of the pressure cup material is [ s ]=303.33MPa, the allowable shear stress is [ t ]=0.5[ s]=151.67MPa For the convenience of calculation, the stress calculation model of the pressure cup assembly is simplified to Figure 5 In the structure shown, when the brake device is working, the pressure plate receives the brake pressure and moves axially toward the brake housing. The pressure cup moves with the brake plate until it contacts the brake housing and provides support for the brake device. The load distribution is as follows: Figure 4 As shown, in this embodiment, the main parameters of the pressure cup assembly are shown in Table 1.

[0024] Table 1

[0025] like Figure 6 As shown, the design method of this embodiment includes: S1. Obtaining the maximum compressive stress of the pressure cup assembly when the compressive stress requirement is met; Specifically, S11. Obtain the load on a single pressure cup assembly based on the total pressure when the brake device is working; obtain the maximum compressive stress of the pressure cup assembly based on the force-bearing area of the disc body, the force-bearing area of the pressure-bearing part and the load on the pressure cup assembly; S12. When the maximum compressive stress meets the compressive stress requirement, the compressive strength of the pressure cup assembly is qualified; if not, adjust the disc body diameter until the adjusted maximum compressive stress meets the compressive stress requirement.

[0026] For example, in a specific embodiment, the step of obtaining the load on a single pressure cup assembly according to the total pressure when the brake device is working in step S11 is: Total pressure when the brake system is working F S for:

[0027] Considering the possible uneven load distribution between the pressure cups and on each pressure cup, the dispersion coefficient is introduced. C =0.75, then the load on a single pressure cup for:

[0028] Where, Indicates the load on a single pressure cup; Indicates the total pressure when the brake device is working; Indicates the total number of pressure cups.

[0029] For example, in a specific embodiment, in step S11, the step of obtaining the maximum compressive stress of the pressure cup assembly according to the force-bearing area of the disc body, the force-bearing area of the pressure-bearing portion, and the load on the pressure cup assembly is as follows: For example, in a specific embodiment, in step S11, the step of obtaining the maximum compressive stress of the pressure cup assembly according to the force-bearing area of the disc body, the force-bearing area of the pressure-bearing portion, and the load on the pressure cup assembly is as follows: The step of obtaining the force-bearing area of the disk of the pressure cup assembly is as follows: according to the disk diameter of the pressure cup assembly, the diameter and number of rivet holes, and the diameter of the pin hole, the force-bearing area of the disk of the pressure cup assembly is obtained. The expression of the force-bearing area of the disk of the pressure cup assembly is:

[0030] Where, Indicates the force-bearing area of the disk of the pressure cup assembly; Indicates the disc diameter of the pressure cup assembly; Indicates the number of rivet holes; Indicates the rivet hole diameter; Indicates the pin hole diameter.

[0031] The step of obtaining the force-bearing area of the pressure-bearing part of the pressure-bearing cup assembly is as follows: according to the bearing width of the pressure-bearing part, the thickness of the pressure-bearing part and the diameter of the pin hole, the force-bearing area of the pressure-bearing part is obtained. That is, the expression of the force-bearing area of the pressure-bearing part is:

[0032] in, Indicates the force-bearing area of the pressure-bearing part; Indicates the thickness of the pressure-bearing part; Indicates the bearing width of the pressure-bearing part; Indicates the pin hole diameter.

[0033] Among them, the steps of obtaining the maximum compressive stress of the pressure cup assembly are: obtaining the stress of the disk body according to the force-bearing area of the disk body and the load borne by the pressure cup assembly; obtaining the stress of the pressure-bearing part according to the force-bearing area of the pressure-bearing part and the load borne by the pressure cup assembly; and taking the maximum compressive stress between the stress of the disk body and the stress of the pressure-bearing part as the maximum compressive stress of the pressure cup assembly.

[0034] For example, in a specific embodiment, the stress of the disc is:

[0035] For example, in a specific embodiment, the stress of the pressure-bearing part is:

[0036] Obviously, the maximum compressive stress s = s A2 = 92.595MPa.

[0037] For example, in a specific embodiment, in step S12, when the maximum compressive stress meets the compressive stress requirement, the compressive strength of the pressure cup assembly is qualified. If not, the diameter of the disc is adjusted until the adjusted maximum compressive stress meets the compressive stress requirement. The steps are: setting the allowable stress of the pressure cup material to [ s ] and the calculated maximum compressive stress s For comparison, if s ]≥ s , the compressive stress of the pressure cup meets the compressive stress requirements; if [ s ]< s , then the compressive stress of the pressure cup does not meet the compressive stress requirement. When the compressive stress requirement is not met, the disk diameter is increased by 1 mm to obtain the adjusted disk diameter and the corresponding pressure surface width, and the adjusted maximum compressive stress is calculated until the adjusted maximum compressive stress meets the compressive stress requirement. The maximum compressive stress that meets the compressive stress requirement is obtained. In this embodiment, [ s ]≥ s A2 , that is, the target maximum compressive stress that meets the compressive stress requirements s 目 = s A2 .

[0038] S2. Obtaining the shear stress of the pressure cup assembly when the shear stress requirement is met; Specifically, S21, obtain the shear stress of the pressure cup assembly based on the shear area of the pressure cup assembly, the force area of the disk body of the pressure cup assembly, the force area of the pressure-bearing part, and the load on the pressure cup assembly; S22, when the shear stress meets the shear stress requirement, the shear strength of the pressure cup assembly is qualified; if not, adjust the thickness of the disk body until the adjusted shear stress meets the shear stress requirement.

[0039] For example, in a specific embodiment, in step S21, the step of obtaining the shear stress of the pressure cup assembly according to the shear area of the pressure cup assembly, the force-bearing area of the disk of the pressure cup assembly, the force-bearing area of the pressure-bearing portion, and the load on the pressure cup assembly is: The steps for obtaining the shear area of the pressure cup assembly are as follows: The shear stress section of the pressure cup is simplified. After simplification, the shear area in this embodiment is:

[0040] Where, represents the shear area of the pressure cup assembly; Indicates the thickness of the disc.

[0041] Then the expression of the shear stress of the pressure cup assembly is:

[0042] For example, in a specific embodiment, in step S22, when the shear stress meets the shear stress requirement, the shear strength of the pressure cup assembly is qualified. If not, the thickness of the disc is adjusted until the adjusted shear stress meets the shear stress requirement. The steps are: setting the shear allowable stress of the pressure cup material to [ t ] and the calculated t For comparison, if t ]≥ t , the shear stress of the pressure cup meets the requirements; if [ t ]< t , then the shear stress of the pressure cup does not meet the use requirements. When the shear stress of the pressure cup does not meet the use requirements, the disc thickness of the pressure cup assembly is increased by 1mm to obtain the adjusted disc thickness. The adjusted shear stress can be obtained according to the adjusted disc thickness until the shear stress meets the shear stress requirements. The target shear stress that meets the shear stress requirements can be obtained. t 目 .

[0043] S3. Obtaining the disk thickness and disk diameter when meeting the strength requirements of the hazardous area; Specifically, based on the maximum compressive stress that meets the compressive stress requirements and the shear stress that meets the shear stress requirements, the principal stress at the root of the pressure-bearing part is obtained, and the equivalent stress is obtained based on the principal stress and the fourth strength theory. If the equivalent stress meets the strength requirements of the hazardous area, the strength of the root of the pressure-bearing part of the pressure cup assembly meets the requirements. If the equivalent stress meets the strength requirements of the hazardous area, the thickness and diameter of the disk body are adjusted at the same time until the adjusted equivalent stress meets the strength requirements of the hazardous area.

[0044] For example, in a specific embodiment, since the analysis process of the maximum compressive stress and shear stress of the pressure cup assembly in steps S2 and S1 shows that the root of the pressure-bearing part in the pressure cup structure is simultaneously subjected to the maximum compressive stress and shear stress, that is, the stress at the root of the pressure-bearing part is in a biaxial stress state, the steps for obtaining the principal stress at the root of the pressure-bearing part are: constructing a biaxial stress state matrix of the root of the pressure-bearing part according to the maximum compressive stress that meets the compressive stress requirements and the shear stress that meets the shear stress requirements; and calculating the characteristic value of the biaxial stress state matrix to obtain the principal stress at the root of the pressure-bearing part.

[0045] Among them, the expression of the biaxial stress state matrix is:

[0046] Among them, the principal stress at the root of the pressure-bearing part is obtained by calculating the characteristic value of the biaxial stress state matrix: the first principal stress at the root of the pressure-bearing part is s 1=-131.99, the second principal stress at the root of the pressure-bearing part s 2=39.40, the third principal stress at the root of the pressure-bearing part s 3=0.

[0047] For example, in one embodiment, the stress s r4 The expression is:

[0048] For example, in a specific implementation, if the equivalent stress meets the strength requirement of the hazardous area, then the strength of the root of the pressure-bearing portion of the pressure cup assembly meets the requirement. If the equivalent stress meets the strength requirement of the hazardous area, then the thickness and diameter of the disc body are adjusted simultaneously until the adjusted equivalent stress meets the strength requirement of the hazardous area. The steps are as follows: Calculate its principal stress and calculate the equivalent stress according to the fourth strength theory s r4 and with the allowable stress [ s ]Compared, if [ s ]≥ s r4 , then the strength of the pressure cup meets the requirements; if [ s ]< s r4 , then the strength of the pressure cup does not meet the requirements; when the strength of the pressure cup does not meet the use requirements, the disk diameter and disk thickness of the pressure cup are increased by 1mm respectively to obtain the adjusted disk diameter and disk thickness, and the adjusted equivalent stress can be obtained based on the adjusted disk diameter and disk thickness. s r4 , until the adjusted equivalent stress is less than or equal to the allowable stress [ s ], at this time the hazardous area meets the design strength requirements.

[0049] After testing, in this embodiment [ s ]≥ s r4 , its dangerous area meets the design strength requirements, and the disk diameter and disk thickness of the pressure cup can be obtained so that the dangerous area meets the design strength requirements.

[0050] S4. Design the pressure cup assembly; Specifically, the pressure cup assembly is designed based on the thickness and diameter of the disc when the equivalent stress meets the strength requirements of the hazardous area.

[0051] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A pressure cup assembly for an aircraft wheel, characterized in that: include: a disc body, on which a pressure-bearing portion is provided; The disc body is used to connect with the pressure disc, and the pressure-bearing part is used to be fixed radially with the brake housing.

2. The pressure cup assembly for an aircraft wheel according to claim 1, characterized in that: The disc body is provided with rivet holes for inserting rivets, and the rivets are used to connect the disc body and the pressure disc.

3. The pressure cup assembly for an aircraft wheel according to claim 2, characterized in that: The pressure-bearing part is an arc-shaped support block, which is arranged in the middle of the disc body. The side of the arc-shaped support block facing away from the disc body is an arc-shaped surface. A pin hole for passing a pin is provided on the arc-shaped support block. The pin is used to connect the arc-shaped support block and the brake housing.

4. The pressure cup assembly for an aircraft wheel according to claim 3, characterized in that: Weight-reducing grooves are provided on the disc bodies on both sides of the arc-shaped support block, wherein the rivet hole is provided in one of the weight-reducing grooves.

5. A design method for a pressure cup assembly for an aircraft wheel, characterized in that: include: Obtain the load on a single pressure cup assembly based on the total pressure when the brake device is working; Obtain the maximum compressive stress of the pressure cup assembly based on the force-bearing area of the disc body, the force-bearing area of the pressure-bearing part, and the load on the pressure cup assembly; When the maximum compressive stress meets the compressive stress requirement, the compressive strength of the pressure cup assembly is qualified. If not, the diameter of the disc body is adjusted until the adjusted maximum compressive stress meets the compressive stress requirement, and the target maximum compressive stress when the compressive stress requirement is met is obtained. Obtaining the shear stress of the pressure cup assembly according to the shear area of the pressure cup assembly, the force-bearing area of the disk of the pressure cup assembly, the force-bearing area of the pressure-bearing part, and the load on the pressure cup assembly; When the shear stress meets the shear stress requirement, the shear strength of the pressure cup assembly is qualified. If not, the thickness of the disc body is adjusted until the adjusted shear stress meets the shear stress requirement, and the target shear stress when the shear stress requirement is met is obtained. According to the target maximum compressive stress and target shear stress, the principal stress at the root of the pressure-bearing part is obtained, and the equivalent stress is obtained according to the principal stress and the fourth strength theory. If the equivalent stress meets the strength requirement of the hazardous area, the strength of the root of the pressure-bearing part of the pressure cup assembly meets the requirement. If the equivalent stress meets the strength requirement of the hazardous area, the thickness and diameter of the disk body are adjusted at the same time until the adjusted equivalent stress meets the strength requirement of the hazardous area. Design the pressure cup assembly based on the disc thickness and disc diameter when the equivalent stress meets the strength requirements of the hazardous area.

6. The method for designing a pressure cup assembly for an aircraft wheel according to claim 5, characterized in that: The steps to obtain the force area of the disk are: The force-bearing area of the disk of the pressure cup assembly is obtained according to the disk diameter of the pressure cup assembly, the diameter and number of the rivet holes, and the diameter of the pin holes.

7. The method for designing a pressure cup assembly for an aircraft wheel according to claim 5, characterized in that: The steps for obtaining the force-bearing area of the pressure-bearing part are: The force-bearing area of the pressure-bearing part is obtained according to the bearing width of the pressure-bearing part, the thickness of the pressure-bearing part and the diameter of the pin hole.

8. The method for designing a pressure cup assembly for an aircraft wheel according to claim 5, characterized in that: The steps to obtain the maximum compressive stress of the pressure cup assembly are: Obtain the stress of the disc body according to the force-bearing area of the disc body and the load on the pressure cup assembly; Obtaining the stress of the pressure-bearing part according to the force-bearing area of the pressure-bearing part and the load on the pressure cup assembly; The maximum compressive stress among the stress of the disk body and the stress of the pressure-bearing part is taken as the maximum compressive stress of the pressure-bearing cup assembly.

9. The method for designing a pressure cup assembly for an aircraft wheel according to claim 5, characterized in that: The steps to obtain the shear area of the pressure cup assembly are: The shear area of the shear stress on the pressure cup is obtained according to the load-bearing width of the arc surface of the pressure-bearing part, the thickness of the pressure-bearing part and the thickness of the disc body.

10. The method for designing a pressure cup assembly for an aircraft wheel according to claim 5, wherein: According to the maximum compressive stress that meets the compressive stress requirements and the shear stress that meets the shear stress requirements, the steps for obtaining the principal stress at the root of the pressure-bearing part are as follows: According to the maximum compressive stress that meets the compressive stress requirements and the shear stress that meets the shear stress requirements, a biaxial stress state matrix of the root of the pressure-bearing part is constructed; The principal stress at the root of the pressure-bearing part is obtained by calculating the characteristic value of the biaxial stress state matrix.

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