Optimization method for fuselage cylinder section end frame shape-preserving frame and storage medium

Abstract

The invention provides an optimization method for a fuselage barrel section end frame shape-preserving frame and a storage medium. The optimization method comprises the following steps that 1, a fuselage barrel section three-dimensional structure model, a shape-preserving tool three-dimensional structure model and a bottom bracket three-dimensional structure model are constructed; step 2, establishing a fuselage cylinder section grid unit, a shape maintaining tool grid unit and a fuselage cylinder section bottom bracket grid unit; thirdly, constraint relations are applied to the machine body barrel section grid units, the shape maintaining tool grid units and the machine body barrel section bottom bracket grid units; 4, solving deformation results of the fuselage cylinder section three-dimensional structure model, the shape-preserving tool three-dimensional structure model and the bottom bracket three-dimensional structure model; and 5, according to the deformation result, changing the geometric form and the material type of the shape-preserving tool three-dimensional structure model, repeating the step 1 to the step 4, completing the calculation of the deformation result of the fuselage cylinder section three-dimensional structure under different shape-preserving tool geometric forms, and selecting the shape-preserving tool three-dimensional structure model with the minimum deformation according to the result.

Description

Technical Field

[0001] This invention relates to, but is not limited to, the field of aircraft component assembly technology, and particularly to an optimization method and storage medium for a conformal frame for fuselage section end frames. Background Technology

[0002] Modern aircraft fuselage sections primarily employ thin-walled cylindrical structures. These structures offer advantages such as light weight and high strength, but also suffer from low stiffness. To control deformation, they are typically placed on specialized brackets during assembly to minimize distortion, and dedicated conformal tooling is designed for support and fixation of the section's end faces. A mechanical interaction exists between the conformal tooling and the fuselage section. If the tooling stiffness is too high, it can cause forced deformation of the fuselage structure, introducing excessive assembly stress. Conversely, if the tooling stiffness is too low, it will fail to provide effective support, negating its conformal purpose. Furthermore, the design must consider the relationship between the tooling's material, weight, geometry, and stiffness; overly bulky tooling can negatively impact operational efficiency and increase costs.

[0003] Traditional conformal tooling design relies heavily on engineers' experience and analogies, lacking quantitative design basis. This experience-driven approach has significant limitations, failing to consider the mechanical interaction between the fuselage section and the conformal tooling, as well as the resulting local assembly deformation. This makes it difficult to accurately reflect the rationality of the conformal tooling design and further optimization directions. To address this issue, it is necessary to consider the geometry of the fuselage section, the dedicated bracket on the underside of the fuselage section, the geometry and material type of the conformal tooling, and the mechanical interaction between the conformal tooling and the fuselage section. An evaluation method for optimizing the conformal tooling design of the fuselage section end frame should be established to provide strong assurance for the assembly quality of thin-walled fuselage sections. Summary of the Invention

[0004] This invention proposes an optimization method for the conformal frame of the fuselage section end frame, which solves the problem that traditional conformal tooling design mainly relies on engineers' experience and analogy methods, and lacks quantitative design basis that takes into account the relationship between the tooling material, weight, geometry and rigidity. It can provide guidance for the design of fuselage assembly scheme and fuselage end frame conformal frame, and avoid assembly deviations caused by excessive deformation of the fuselage end frame and insufficient rigidity of the end frame conformal frame. It is an effective optimization method.

[0005] The technical solution of this invention is as follows: In a first aspect, this application provides an optimization method for a conformal frame for the end frame of a fuselage section, comprising the following steps: Step 1: Construct the three-dimensional structural model of the fuselage section (1), the three-dimensional structural model of the conformal tooling (2), and the three-dimensional structural model of the bottom bracket (3). Step 2: Mesh the three-dimensional structural model (1) of the fuselage section, the three-dimensional structural model (2) of the conformal tooling, and the three-dimensional structural model (3) of the bottom bracket to obtain the fuselage section mesh unit (4), the conformal tooling mesh unit (5), and the fuselage section bottom bracket mesh unit (6). Step 3: Apply constraints to the fuselage section grid unit (4), the conformal tooling grid unit (5), and the fuselage section bottom bracket grid unit (6); Step 4: Solve the deformation results of the three-dimensional structural model (1) of the fuselage section, the three-dimensional structural model (2) of the conformal tooling, and the three-dimensional structural model (3) of the bottom bracket; Step 5: Based on the deformation results, change the geometry and material type of the conformal tooling three-dimensional structural model (2), repeat steps 1 to 4, and complete the calculation of the deformation results of the fuselage section three-dimensional structure under different conformal tooling geometry. Based on the results, select the conformal tooling three-dimensional structural model (2) with the smallest deformation.

[0006] Specifically, step one includes: Step 1-1: Create a 1:1 scale 3D structural model of the fuselage section, a 3D structural model of the conformal tooling, and a 3D structural model of the bottom bracket in CAE software. Step 1-2: After deleting the chamfers, bosses, gaskets, and bolts from the geometric model, import it into the finite element simulation software; Steps 1-3: Set material property parameters based on the materials of the fuselage section, conformal tooling, and bottom bracket. The material property parameters include Young's modulus, Poisson's ratio, and density.

[0007] Specifically, the three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket in step 1-1 have the following requirements: The weights of the fuselage section 3D structural model, the conformal tooling 3D structural model, and the bottom bracket 3D structural model are consistent with the actual weights, and the deviations of the length, width, and height of the outer dimensions from the actual dimensions are no more than 20%.

[0008] Specifically, step two includes: Step 2-1: The maximum dimensions of the mesh in the three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket do not exceed 1% of the length, width, and height of their respective models; Step 2-2: Set constraints at the bottom of the bracket to limit 6 degrees of freedom, and the entire model is supported by the bottom bracket.

[0009] Specifically, step 2-1 has the following requirements: All mesh cell dimensions must be checked, and the minimum value of the mesh cell in the fuselage section 3D structural model must not exceed the maximum value of the mesh cell in the conformal tooling 3D structural model.

[0010] Specifically, step three includes: Step 3-1, the constraint equation between the inner surface of the fuselage section 3D structural model and the outer surface of the conformal tooling 3D structural model is:

[0011] in, , , These represent the three displacement components of the aircraft in the heading, span, and gravitational direction, respectively; superscript M 1 and S 1 represents the inner surface of the fuselage section's three-dimensional structural model and the outer surface of the conformal tooling's three-dimensional structural model, respectively; Step 3-2, the constraint equations between the upper surface of the bottom bracket 3D structural model and the lower surface of the fuselage section 3D structural model are:

[0012] in, , , These represent the three displacement components of the aircraft in the heading, span, and gravitational direction, respectively; superscript M 2 and S 2 represents the upper surface of the bottom bracket 3D structural model and the lower surface of the fuselage section 3D structural model, respectively.

[0013] Specifically, step four has the following requirements: Step 4-1: Apply gravity loads to the three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket. Step 4-2: Solve the problem using the static displacement method to calculate the deformation of the entire model under gravity load; Step 4-3: Record the maximum displacement results of the three-dimensional structural model of the fuselage section. .

[0014] Specifically, step five has the following requirements: 5-1 Keep the three-dimensional structural model of the fuselage section and the bottom bracket unchanged, and only maintain the geometric form of the three-dimensional structural model of the tooling. 5-2 Repeat steps one through four to calculate the maximum displacement of the fuselage section three-dimensional structural model under different geometric forms of the conformal tooling with different heights, widths, and wall thicknesses; 5-3 All of the above obtained Compare the numerical values; the smallest value... The corresponding conformal tooling geometry is the conformal tooling three-dimensional structural model with minimal deformation (2).

[0015] Secondly, this application provides a computer-readable storage medium, including: a memory and a processor; wherein, the memory is used to store a computer-readable program; and the processor is used to implement, when executing the computer-readable program, the evaluation method for the optimized design of the fuselage section end frame conformal frame as described above.

[0016] This invention proposes an optimization method and storage medium for a conformal tooling for fuselage section end frame. This addresses the problem that traditional conformal tooling design mainly relies on engineers' experience and analogy methods, lacking quantitative design basis that takes into account the relationship between tooling material, weight, geometry, and rigidity. It can provide guidance for fuselage assembly scheme design and fuselage end frame conformal tooling design, avoiding assembly deviations caused by excessive fuselage end frame deformation or insufficient rigidity of the end frame conformal tooling. This is an effective optimization method. Attached Figure Description

[0017] Figure 1 This is a flowchart of an optimization method for a conformal frame for the end frame of a fuselage section, as proposed in this invention. Figure 2 This is to construct the three-dimensional structural model of the fuselage section, the three-dimensional structural model of the conformal tooling, and the three-dimensional structural model of the bottom bracket in step one of this invention; Figure 3 Mesh the various simplified 3D models in step two of this invention; Figure 4 The deformation result is calculated in step four of this invention; The numbers in the diagram are explained as follows: 1. Fuselage section; 2. Conformal tooling; 3. Bottom bracket of fuselage section; 4. Grid unit of fuselage section; 5. Grid unit of conformal tooling; 6. Grid unit of bottom bracket of fuselage section. Detailed Implementation

[0018] As explained in the background section, the evaluation method for optimizing the conformal jig design of fuselage section end frames plays a crucial role. Traditional conformal jig design relies heavily on engineers' experience and analogies, lacking quantitative design basis and failing to consider the mechanical interaction between the fuselage section and the conformal jig, as well as the resulting local assembly deformation. This makes it difficult to accurately reflect the rationality of the conformal jig design and further optimization directions. Therefore, it is necessary to consider the geometry of the fuselage section, the dedicated bracket on the underside of the fuselage section, the geometry and material type of the conformal jig, and the mechanical interaction between the conformal jig and the fuselage section. Establishing an evaluation method for optimizing the conformal jig design of fuselage section end frames provides strong assurance for the assembly quality of thin-walled fuselage sections. The invention will now be further described in detail with reference to the accompanying drawings and specific embodiments.

[0019] Example 1 This application provides an optimization method for a conformal frame for the end frame of a fuselage section, comprising the following steps: Step 1: Construct the three-dimensional structural model of the fuselage section (1), the three-dimensional structural model of the conformal tooling (2), and the three-dimensional structural model of the bottom bracket (3). Step 2: Mesh the three-dimensional structural model (1) of the fuselage section, the three-dimensional structural model (2) of the conformal tooling, and the three-dimensional structural model (3) of the bottom bracket to obtain the fuselage section mesh unit (4), the conformal tooling mesh unit (5), and the fuselage section bottom bracket mesh unit (6). Step 3: Apply constraints to the fuselage section grid unit (4), the conformal tooling grid unit (5), and the fuselage section bottom bracket grid unit (6); Step 4: Solve the deformation results of the three-dimensional structural model (1) of the fuselage section, the three-dimensional structural model (2) of the conformal tooling, and the three-dimensional structural model (3) of the bottom bracket; Step 5: Based on the deformation results, change the geometry and material type of the conformal tooling three-dimensional structural model (2), repeat steps 1 to 4, and complete the calculation of the deformation results of the fuselage section three-dimensional structure under different conformal tooling geometry. Based on the results, select the conformal tooling three-dimensional structural model (2) with the smallest deformation.

[0020] Specifically, step one includes: Step 1-1: Create a 1:1 scale 3D structural model of the fuselage section, a 3D structural model of the conformal tooling, and a 3D structural model of the bottom bracket in CAE software. Step 1-2: After deleting the chamfers, bosses, gaskets, and bolts from the geometric model, import it into the finite element simulation software; Steps 1-3: Set material property parameters based on the materials of the fuselage section, conformal tooling, and bottom bracket. The material property parameters include Young's modulus, Poisson's ratio, and density.

[0021] Specifically, the three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket in step 1-1 have the following requirements: The weights of the fuselage section 3D structural model, the conformal tooling 3D structural model, and the bottom bracket 3D structural model are consistent with the actual weights, and the deviations of the length, width, and height of the outer dimensions from the actual dimensions are no more than 20%.

[0022] Specifically, step two includes: Step 2-1: The maximum dimensions of the mesh in the three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket do not exceed 1% of the length, width, and height of their respective models; Step 2-2: Set constraints at the bottom of the bracket to limit 6 degrees of freedom, and the entire model is supported by the bottom bracket.

[0023] Specifically, step 2-1 has the following requirements: All mesh cell dimensions must be checked, and the minimum value of the mesh cell in the fuselage section 3D structural model must not exceed the maximum value of the mesh cell in the conformal tooling 3D structural model.

[0024] Specifically, step three includes: Step 3-1, the constraint equation between the inner surface of the fuselage section 3D structural model and the outer surface of the conformal tooling 3D structural model is:

[0025] in, , , These represent the three displacement components of the aircraft in the heading, span, and gravitational direction, respectively; superscript M 1 and S 1 represents the inner surface of the fuselage section's three-dimensional structural model and the outer surface of the conformal tooling's three-dimensional structural model, respectively; Step 3-2, the constraint equations between the upper surface of the bottom bracket 3D structural model and the lower surface of the fuselage section 3D structural model are:

[0026] in, , , These represent the three displacement components of the aircraft in the heading, span, and gravitational direction, respectively; superscript M 2 and S 2 represents the upper surface of the bottom bracket 3D structural model and the lower surface of the fuselage section 3D structural model, respectively.

[0027] Specifically, step four has the following requirements: Step 4-1: Apply gravity loads to the three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket. Step 4-2: Solve the problem using the static displacement method to calculate the deformation of the entire model under gravity load; Step 4-3: Record the maximum displacement results of the three-dimensional structural model of the fuselage section. .

[0028] Specifically, step five has the following requirements: 5-1 Keep the three-dimensional structural model of the fuselage section and the bottom bracket unchanged, and only maintain the geometric form of the three-dimensional structural model of the tooling. 5-2 Repeat steps one through four to calculate the maximum displacement of the fuselage section three-dimensional structural model under different geometric forms of the conformal tooling with different heights, widths, and wall thicknesses; 5-3 All of the above obtained Compare the numerical values; the smallest value... The corresponding conformal tooling geometry is the conformal tooling three-dimensional structural model with minimal deformation (2).

[0029] In summary, this invention discloses an optimization method for a conformal fitting for the end frame of a fuselage section. The method includes the following steps: constructing a three-dimensional structural model of the fuselage section, a three-dimensional structural model of the conformal fitting fixture, and a three-dimensional structural model of the bottom bracket; performing mesh generation; applying constraints; solving for the deformation results of the three-dimensional structural models of the fuselage section, the conformal fitting fixture, and the bottom bracket; changing the geometric form and material type of the conformal fitting fixture's three-dimensional structural model (height, width, wall thickness, etc.), and repeating steps one through four to complete the calculation of the deformation results of the three-dimensional structure of the fuselage section under different conformal fitting geometric forms; and selecting the optimal conformal fitting design scheme based on the results. This method considers the geometry of the fuselage section, the dedicated bracket on the underside of the fuselage section, the geometry and material type of the conformal tooling, and the mechanical interaction between the conformal tooling and the fuselage section. It also takes into account the quantitative relationship between the material, weight, geometry and rigidity of the tooling, providing guidance for the design of the fuselage assembly scheme and the conformal frame of the fuselage end frame. This method avoids assembly deviations caused by excessive deformation of the fuselage end frame and insufficient rigidity of the conformal frame, and is an effective optimization method.

[0030] Example 2 like Figure 1-4 As shown, an optimization method for a conformal frame for the end frame of a fuselage section includes the following steps: Step 1: Construct the three-dimensional structural model of the fuselage section, the three-dimensional structural model of the conformal tooling, and the three-dimensional structural model of the bottom bracket; Step 2: Mesh the three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket. Step 3: Apply constraints to the three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket. Step 4: Solve for the deformation results of the three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket. Step 5: Change the geometric form and material type of the conformal tooling 3D structural model, such as height, width, and wall thickness. Repeat steps 1 to 4 to complete the calculation of the deformation results of the fuselage section 3D structure under different conformal tooling geometric forms. Select the best conformal tooling design scheme based on the results.

[0031] Specifically, step one includes: Step 1-1: In ABAQUS 2018 software, create a 1:1 three-dimensional structural model of the fuselage section, a 3D structural model of the conformal tooling, and a 3D structural model of the bottom bracket, all of which are identical to the actual object. Step 1-2: After deleting the chamfers, bosses, gaskets, and bolts from the geometric model, import it into the finite element simulation software; Steps 1-3: Set material property parameters based on the materials of the fuselage section, conformal tooling, and bottom bracket, including Young's modulus, Poisson's ratio, and density. In this embodiment, the Young's modulus and Poisson's ratio of the fuselage section are 70 GPa and 0.30, respectively, and the material density is 2.1 × 10⁻⁶. -9 t / mm 3 The conformal tooling and bottom bracket have a Young's modulus of 210 GPa and a Poisson's ratio of 0.25, and a density of 7.8 × 10⁻⁶. -9 t / mm 3 ; Specifically, the three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket in step 1-1 have the following requirements: The weights of the fuselage section 3D structural model, the conformal tooling 3D structural model, and the bottom bracket 3D structural model are consistent with the actual weights, and the deviations of the length, width, and height of the outer dimensions from the actual dimensions are no more than 20%.

[0032] Specifically, step two includes: Step 2-1: The maximum dimensions of the mesh in the three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket do not exceed 1% of the length, width, and height of their respective models; Step 2-2: Set constraints at the bottom of the bracket to limit 6 degrees of freedom, and the entire model is supported by the bottom bracket.

[0033] Specifically, step 2-1 has the following requirements: All mesh cell dimensions must be checked, and the minimum value of the mesh cell in the fuselage section 3D structural model must not exceed the maximum value of the mesh cell in the conformal tooling 3D structural model.

[0034] Specifically, step three includes: Step 3-1, the constraint equation between the inner surface of the fuselage section 3D structural model and the outer surface of the conformal tooling 3D structural model is:

[0035] in, , , These represent the three displacement components of the aircraft in the heading, span, and gravitational direction, respectively; superscript M 1 and S 1 represents the inner surface of the fuselage section's three-dimensional structural model and the outer surface of the conformal tooling's three-dimensional structural model, respectively; Step 3-2, the constraint equations between the upper surface of the bottom bracket 3D structural model and the lower surface of the fuselage section 3D structural model are:

[0036] in, , , These represent the three displacement components of the aircraft in the heading, span, and gravitational direction, respectively; superscript M 2 and S 2 represents the upper surface of the bottom bracket 3D structural model and the lower surface of the fuselage section 3D structural model, respectively.

[0037] Specifically, step four has the following requirements: Step 4-1: Apply gravity loads to the three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket. Step 4-2: Solve the problem using the static displacement method to calculate the deformation of the entire model under gravity load.

[0038] Step 4-3: Record the maximum displacement results of the three-dimensional structural model of the fuselage section. .

[0039] Specifically, step five has the following requirements: 5-1 Keep the three-dimensional structural model of the fuselage section and the bottom bracket unchanged, and only maintain the geometric form of the three-dimensional structural model of the tooling. 5-2 Repeat steps one through four to calculate the maximum displacement of the fuselage section three-dimensional structural model under different geometric forms such as height, width, and wall thickness of the conformal tooling.

[0040] 5-3 All of the above obtained Compare the numerical values; the smallest value... The corresponding conformal tooling geometry is the optimal conformal tooling design scheme.

[0041] This application provides a computer-readable storage medium, including: a memory and a processor; wherein, the memory is used to store a computer-readable program; and the processor is used to implement, when executing the computer-readable program, the evaluation method for the optimized design of the fuselage section end frame conformal frame as described above.

[0042] The above description, in conjunction with specific preferred embodiments, provides a further detailed explanation of the present invention. It should not be construed that the specific implementation of the present invention is limited to these descriptions. For those skilled in the art, various simple deductions or substitutions can be made without departing from the concept of the present invention, and all such modifications and substitutions should be considered within the scope of protection of the present invention.

[0043] The parts not covered in this invention are the same as or can be implemented using existing technologies.

Claims

1. An optimization method for a conformal frame for the end frame of a fuselage section, characterized in that, Includes the following steps: Step 1: Construct the three-dimensional structural model of the fuselage section (1), the three-dimensional structural model of the conformal tooling (2), and the three-dimensional structural model of the bottom bracket (3). Step 2: Mesh the three-dimensional structural model (1) of the fuselage section, the three-dimensional structural model (2) of the conformal tooling, and the three-dimensional structural model (3) of the bottom bracket to obtain the fuselage section mesh unit (4), the conformal tooling mesh unit (5), and the fuselage section bottom bracket mesh unit (6). Step 3: Apply constraints to the fuselage section grid unit (4), the conformal tooling grid unit (5), and the fuselage section bottom bracket grid unit (6); Step 4: Solve the deformation results of the three-dimensional structural model (1) of the fuselage section, the three-dimensional structural model (2) of the conformal tooling, and the three-dimensional structural model (3) of the bottom bracket; Step 5: Based on the deformation results, change the geometry and material type of the conformal tooling three-dimensional structural model (2), repeat steps 1 to 4, and complete the calculation of the deformation results of the fuselage section three-dimensional structure under different conformal tooling geometry. Based on the results, select the conformal tooling three-dimensional structural model (2) with the smallest deformation.

2. The optimization method for the conformal frame of the fuselage section end frame according to claim 1, characterized in that, Step one includes: Step 1-1: Create a 1:1 scale 3D structural model of the fuselage section, a 3D structural model of the conformal tooling, and a 3D structural model of the bottom bracket in CAE software. Step 1-2: After deleting the chamfers, bosses, gaskets, and bolts from the geometric model, import it into the finite element simulation software; Steps 1-3: Set material property parameters based on the materials of the fuselage section, conformal tooling, and bottom bracket. The material property parameters include Young's modulus, Poisson's ratio, and density.

3. The optimization method for the end frame conformal frame of the fuselage section according to claim 2, characterized in that, The three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket in step 1-1 have the following requirements: The weights of the fuselage section 3D structural model, the conformal tooling 3D structural model, and the bottom bracket 3D structural model are consistent with the actual weights, and the deviations of the length, width, and height of the outer dimensions from the actual dimensions are no more than 20%.

4. The optimization method for the conformal frame of the fuselage section end frame according to claim 1, characterized in that, Step two includes: Step 2-1: The maximum dimensions of the mesh in the three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket do not exceed 1% of the length, width, and height of their respective models; Step 2-2: Set constraints at the bottom of the bracket to limit 6 degrees of freedom, and the entire model is supported by the bottom bracket.

5. The optimization method for the conformal frame of the fuselage section end frame according to claim 4, characterized in that, Step 2-1 has the following requirements: All mesh cell dimensions must be checked, and the minimum value of the mesh cell in the fuselage section 3D structural model must not exceed the maximum value of the mesh cell in the conformal tooling 3D structural model.

6. The optimization method for the conformal frame of the fuselage section end frame according to claim 4, characterized in that, Step three includes: Step 3-1, the constraint equation between the inner surface of the fuselage section 3D structural model and the outer surface of the conformal tooling 3D structural model is: in, These represent the three displacement components of the aircraft in the heading, span, and gravitational direction, respectively; superscript M 1 and S 1 represents the inner surface of the fuselage section's three-dimensional structural model and the outer surface of the conformal tooling's three-dimensional structural model, respectively; Step 3-2, the constraint equations between the upper surface of the bottom bracket 3D structural model and the lower surface of the fuselage section 3D structural model are: in, These represent the three displacement components of the aircraft in the heading, span, and gravitational direction, respectively; superscript M 2 and S 2 represents the upper surface of the bottom bracket 3D structural model and the lower surface of the fuselage section 3D structural model, respectively.

7. The optimization method for the conformal frame of the fuselage section end frame according to claim 2, characterized in that, Step four has the following requirements: Step 4-1: Apply gravity loads to the three-dimensional structural models of the fuselage section, the conformal tooling, and the bottom bracket. Step 4-2: Solve the problem using the static displacement method to calculate the deformation of the entire model under gravity load; Step 4-3: Record the maximum displacement results of the three-dimensional structural model of the fuselage section.

8. The optimization method for the conformal frame of the fuselage section end frame according to claim 2, characterized in that, Step five has the following requirements: 5-1 Keep the three-dimensional structural model of the fuselage section and the bottom bracket unchanged, and only maintain the geometric form of the three-dimensional structural model of the tooling. 5-2 Repeat steps one through four to calculate the maximum displacement of the fuselage section three-dimensional structural model under different geometric forms of the conformal tooling with different heights, widths, and wall thicknesses; 5-3 All of the above obtained Compare the numerical values; the smallest value... The corresponding conformal tooling geometry is the conformal tooling three-dimensional structural model with minimal deformation (2).

9. A computer-readable storage medium, characterized in that, include: Memory and processor; The memory is used to store computer-readable programs; The processor is configured to, when executing a computer-readable program, implement the evaluation method for the conformal design optimization of the fuselage section end frame as described in any one of claims 1 to 8.

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