A quantitative design method for the stiffness of a wing tooling flag

Abstract

This invention discloses a quantitative design method for the stiffness of an airfoil tooling flag, comprising: Step 1, establishing a three-dimensional geometric model of the tooling flag, and obtaining a simplified model of the airfoil tooling flag by simplifying the three-dimensional geometric model; Step 2, setting mechanical boundary conditions for the simplified model of the airfoil tooling flag; Step 3, establishing constraint equations based on the simplified model of the airfoil tooling flag and the location of the load application points in the model; Step 4, solving for the displacement field results of the simplified model of the airfoil tooling flag under the concentrated load by applying a concentrated load based on the load application points of the simplified model of the tooling flag; Step 5, meshing the simplified model of the tooling flag and post-processing the data of the mesh elements, including: using the displacement field results obtained in Step 4 and the mesh elements divided by the simplified model of the airfoil tooling flag to obtain the displacement matrix and total mass of the simplified model of the airfoil tooling flag; Step 6, calculating the optimal tooling flag design scheme that meets the stiffness index requirements by combining the structural parameters in the simplified model of the airfoil tooling flag and using the calculation method in Step 5. The technical solution provided by this invention selects the optimal parameter scheme in the design based on the calculation results, reduces the weight of the tooling flag while ensuring the stiffness of the tooling flag, avoids structural deformation caused by insufficient stiffness of the tooling flag, and the proposed quantitative stiffness design method can provide a theoretical basis for optimization design, which is a fast and effective design method.

Description

Technical Field

[0001] This invention relates to, but is not limited to, the field of tooling design technology, and particularly to a method for quantitative stiffness design of tooling flags for airfoils. Background Technology

[0002] To ensure high-quality wing assembly, wing assembly fixtures typically include a fixture flag. This flag connects the wing junction to the fixture body and directly impacts assembly accuracy and stability. To prevent deformation of the fixture flag during use, which could lead to a decrease in assembly accuracy, the flag's structure needs to be optimized.

[0003] Currently, the traditional design method for tooling flags is determined by human experience. Due to the lack of mathematical relationship between design parameters and structural stiffness, the rigidity of tooling flags is usually increased by increasing the cross-sectional area of ​​the end face of the tooling flag and selecting higher strength materials. This increases the weight of the entire tooling flag, increases manufacturing costs, and may also lead to excessive rigidity of the tooling flag, which may cause uncoordinated deformation of the entire assembly system. Summary of the Invention

[0004] The purpose of this invention is to solve the above-mentioned technical problems. This invention provides a quantitative design method for the stiffness of a wing tooling flag, which solves the problems of existing tooling flag designs. These designs increase the stiffness of the tooling flag by increasing the cross-sectional area of ​​the end face and selecting higher strength materials, thereby increasing the weight of the entire tooling flag, increasing manufacturing costs, and potentially causing excessive stiffness of the tooling flag, which in turn causes uncoordinated deformation of the entire assembly system.

[0005] The technical solution of the present invention: In a first aspect, embodiments of the present invention provide a method for quantitative design of stiffness for a wing tooling flag, comprising:

[0006] Step 1: Establish a three-dimensional geometric model of the tooling flag, and obtain a simplified model of the wing tooling flag by simplifying the three-dimensional geometric model.

[0007] Step 2: Set mechanical boundary conditions for the simplified model of the wing tooling flag;

[0008] Step 3: Based on the simplified model of the wing tooling flag and the location of the load application points in the model, establish constraint equations;

[0009] Step 4: By applying a concentrated load to the load application point based on the simplified tooling flag model, the displacement field results of the simplified wing tooling flag model under the concentrated load are obtained.

[0010] Step 5 involves meshing the simplified model of the tooling flag and post-processing the mesh cells, including: using the displacement field results obtained in Step 4 and the mesh cells divided from the simplified model of the wing tooling flag, to obtain the displacement matrix and total mass of the simplified model of the wing tooling flag.

[0011] Step six: By combining the structural parameters in the simplified model of the wing tooling flag, the optimal tooling flag design scheme that meets the stiffness index requirements is calculated using the calculation method in step five.

[0012] Optionally, in the quantitative stiffness design method for a wing tooling flag as described above, step one includes:

[0013] Step 1-1: Use CAD software to create a three-dimensional geometric model of the wing tooling flag. In the three-dimensional geometric model, delete all parts except bolts and gaskets in the wing tooling flag model to obtain a simplified model of the wing tooling flag.

[0014] Steps 1-2: Set a load application point at the center of the end face in the simplified model of the wing tooling flag; the load application point is used as the load application point of the simplified model of the wing tooling flag in subsequent finite element calculations.

[0015] Optionally, in the quantitative stiffness design method for wing tooling flags as described above, the simplified model of the wing tooling flag obtained in step 1-1 has the following requirements:

[0016] The simplified model must have the same length, width, and height as the actual wing tooling flag, and the simplified model must have the same end plate, tooling flag rib, tooling flag front face, and bolt hole positions as the actual wing tooling flag.

[0017] Optionally, in the method for quantitative stiffness design of a wing tooling flag as described above, step two includes:

[0018] Step 2-1: Based on the material type in the simplified model of the wing tooling flag, set the Young's modulus, Poisson's ratio, and material density of the actual wing tooling flag.

[0019] Step 2-2: Set 6-DOF constraints at the bolt hole positions in the simplified model of the wing tooling flag as the mechanical boundary conditions of the simplified model of the wing tooling flag.

[0020] Optionally, in the quantitative stiffness design method for a wing tooling flag as described above, step three includes:

[0021] Based on the location of the load application point in the simplified model of the wing tooling flag, the constraint equations for the simplified model of the wing tooling flag at the load application point and the leading edge face of the tooling flag are as follows:

[0022]

[0023] Where u1, u2, and u3 represent the three displacement components of the aircraft in the heading, span, and gravity directions, respectively; the superscripts F and w represent the tooling flag and the load application point, respectively; and λ is the set value of the periodic boundary condition.

[0024] Optionally, in the method for quantitative stiffness design of a wing tooling flag as described above, step four includes:

[0025] Step 4-1: Divide the simplified model of the wing tooling flag into mesh cells. The maximum dimensions of the mesh cells in the simplified model of the wing tooling flag shall not exceed 10% of the length, width and height of the wing tooling flag.

[0026] Step 4-2: Input the mechanical boundary conditions and constraint equations into the finite element software, apply a concentrated load to the load application point of the simplified model of the wing tooling flag, and solve it using the statics method to obtain the displacement field results of the simplified model of the wing tooling flag under the concentrated load.

[0027] Optionally, in the quantitative design method for stiffness of a wing tooling flag as described above, step five includes:

[0028] Step 5-1: Number each mesh element in the simplified model of the wing tooling flag. Based on the calculation results in Step 4, store the displacement components corresponding to each mesh element number into the displacement matrix [U], resulting in:

[0029]

[0030] The first column lists the mesh element numbers from 1 to n in the simplified model of the wing tooling flag; the second to fourth columns list the displacement components corresponding to the mesh element numbers, where u i,1 u i,2 u i,3 These represent the displacement components of the i-th grid cell in the heading, span, and gravity directions, respectively.

[0031] Step 5-2: Based on the mass of each mesh element in the simplified model of the wing tooling flag, calculate the total mass m of the entire simplified tooling flag model as follows:

[0032]

[0033] in, Let be the mass of the i-th mesh element in the simplified model of the wing tooling flag, and n be the total number of mesh elements in the simplified model of the wing tooling flag.

[0034] Step 5-3: Using a statistical algorithm, the maximum value in the displacement matrix [U] of the simplified model of the wing tooling flag is obtained as the stiffness index of the simplified model of the tooling flag, and the mass of the tooling flag is used as the weight index of the tooling flag.

[0035] Optionally, in the quantitative stiffness design method for a wing tooling flag as described above, step six, establishing the quantitative stiffness design method for the tooling flag, includes the following steps:

[0036] Step 6-1: List the structural parameters that need to be designed for the simplified model of the wing tooling flag and their value ranges, including the length, width, height, material type, and tooling flag rib form of the simplified model of the wing tooling flag.

[0037] Step 6-2: Take all structural parameters to be designed and their value ranges as input conditions, repeat steps 5-1 to 5-3, and calculate the tooling stiffness index and weight index corresponding to each structural parameter design combination in turn.

[0038] Step 6-3: Based on the calculation results in Step 6-2, select the minimum weight that meets the stiffness index requirements of the tooling flag as the optimal tooling flag design scheme before designing the tooling flag.

[0039] In a second aspect, embodiments of the present invention also provide a computer-readable storage medium, including: a memory and a processor;

[0040] The memory is used to store computer-readable programs;

[0041] The processor is configured to implement, when executing a computer-readable program, the method for quantitative stiffness design of a wing tooling flag as described in any of the preceding claims.

[0042] The beneficial effects of this invention are as follows: Based on efficient simulation technology, this invention provides a quantitative design method for the stiffness of wing tooling flags. Considering factors such as the flag's form, geometry, material, weight, and the location and magnitude of external loads, a simplified model of the tooling flag is established. Efficient simulation calculations are then performed, meaning that every structural parameter required for the tooling flag design is calculated before the formal design phase. Post-processing is then performed on the mesh element data of the simplified tooling flag model. Based on the calculation results of the structural parameters, the optimal parameter scheme is selected in the design, reducing the flag's weight while ensuring its stiffness, thus avoiding structural deformation caused by insufficient stiffness. The quantitative design method for the stiffness of wing tooling flags provided by this invention provides a theoretical basis for optimized design and is a fast and effective design method. Attached Figure Description

[0043] The accompanying drawings are used to provide a further understanding of the technical solution of the present invention and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present invention and do not constitute a limitation on the technical solution of the present invention.

[0044] Figure 1 This is a flowchart of a method for quantitative stiffness design of a wing tooling flag proposed in this invention;

[0045] Figure 2 A schematic diagram of the finite element model of the wing tooling flag in the quantitative stiffness design method for the wing tooling flag provided in the embodiment of the present invention;

[0046] Figure 3 A schematic diagram of the finite element mesh model in the method for quantitative stiffness design of wing tooling flags provided in an embodiment of the present invention;

[0047] Figure 4 This is a schematic diagram showing the mass of the tooling flag calculated under different design widths in the quantitative design method for stiffness of the tooling flag for an airfoil provided in an embodiment of the present invention.

[0048] Figure 5 This is a schematic diagram showing the displacement of the tooling flag under different materials, calculated in the quantitative design method for stiffness of the tooling flag for the wing provided in the embodiments of the present invention.

[0049] Explanation of reference numerals in the attached figures:

[0050] 1. Wing tooling flag; 2. Tooling flag end plate; 3. Tooling flag rib; 4. Tooling flag front end face; 5. Bolt holes; 6. Grid unit. Detailed Implementation

[0051] To make the purpose, technical solutions and advantages of the present invention more clearly understood, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that, unless there is a conflict, the embodiments and features in the embodiments of the present application can be combined with each other in any manner.

[0052] The background section has already explained the important role of wing tooling flags in wing assembly and the necessity of their structural design. Addressing the numerous problems with existing tooling flag design methods, this invention provides a quantitative stiffness design method for wing tooling flags; specifically, it is a tooling flag design method that incorporates efficient stiffness calculation results.

[0053] The present invention provides the following specific embodiments, which can be combined with each other. For the same or similar concepts or processes, they may not be described again in some embodiments.

[0054] Figure 1This is a flowchart illustrating a quantitative stiffness design method for a wing tooling flag proposed in this invention. The quantitative stiffness design method for a wing tooling flag provided in this embodiment of the invention includes the following steps:

[0055] Step 1: Establish a three-dimensional geometric model of the tooling flag, and obtain a simplified model of the wing tooling flag by simplifying the three-dimensional geometric model.

[0056] Step 2: Set mechanical boundary conditions for the simplified model of the wing tooling flag;

[0057] Step 3: Based on the simplified model of the wing tooling flag and the location of the load application points in the model, establish constraint equations;

[0058] Step 4: By applying a concentrated load to the load application point based on the simplified tooling flag model, the displacement field results of the simplified wing tooling flag model under the concentrated load are obtained.

[0059] Step 5 involves meshing the simplified model of the tooling flag and post-processing the mesh cells, including: using the displacement field results obtained in Step 4 and the mesh cells divided from the simplified model of the wing tooling flag, to obtain the displacement matrix and total mass of the simplified model of the wing tooling flag.

[0060] Step six: By combining the structural parameters in the simplified model of the wing tooling flag, the optimal tooling flag design scheme that meets the stiffness index requirements is calculated using the calculation method in step five.

[0061] In one implementation of this invention, the process of step one above may include:

[0062] Step 1-1: Use CAD software to create a three-dimensional geometric model of the wing tooling flag. In the three-dimensional geometric model, delete all parts except bolts and gaskets in the wing tooling flag model to obtain a simplified model of the wing tooling flag.

[0063] Steps 1-2: Set a load application point at the center of the end face in the simplified model of the wing tooling flag; the load application point is used as the load application point of the simplified model of the wing tooling flag in subsequent finite element calculations.

[0064] In the specific implementation of this method, the simplified model of the wing tooling flag obtained in step 1-1 has the following requirements:

[0065] The simplified model must have the same length, width, and height as the actual wing tooling flag, and the simplified model must have the same end plate, tooling flag rib, tooling flag front face, and bolt hole positions as the actual wing tooling flag.

[0066] In one implementation of this invention, the process of step two above may include:

[0067] Step 2-1: Based on the material type in the simplified model of the wing tooling flag, set the Young's modulus, Poisson's ratio, and material density of the actual wing tooling flag.

[0068] Step 2-2: Set 6-DOF constraints at the bolt hole positions in the simplified model of the wing tooling flag as the mechanical boundary conditions of the simplified model of the wing tooling flag.

[0069] In one implementation of this invention, step three may include:

[0070] Based on the location of the load application point in the simplified model of the wing tooling flag, the constraint equations for the simplified model of the wing tooling flag at the load application point and the leading edge face of the tooling flag are as follows:

[0071]

[0072] Where u1, u2, and u3 represent the three displacement components of the aircraft in the heading, span, and gravity directions, respectively; the superscripts F and w represent the tooling flag and the load application point, respectively; and λ is the set value of the periodic boundary condition.

[0073] In one implementation of this invention, step four may include:

[0074] Step 4-1: Divide the simplified model of the wing tooling flag into mesh cells. The maximum dimensions of the mesh cells in the simplified model of the wing tooling flag shall not exceed 10% of the length, width and height of the wing tooling flag.

[0075] Step 4-2: Input the mechanical boundary conditions and constraint equations into the finite element software, apply a concentrated load to the load application point of the simplified model of the wing tooling flag, and solve it using the statics method to obtain the displacement field results of the simplified model of the wing tooling flag under the concentrated load.

[0076] In one implementation of this invention, step five may include:

[0077] Step 5-1: Number each mesh element in the simplified model of the wing tooling flag. Based on the calculation results in Step 4, store the displacement components corresponding to each mesh element number into the displacement matrix [U], resulting in:

[0078]

[0079] The first column lists the mesh element numbers from 1 to n in the simplified model of the wing tooling flag; the second to fourth columns list the displacement components corresponding to the mesh element numbers, where u i,1 u i,2 u i,3These represent the displacement components of the i-th grid cell in the heading, span, and gravity directions, respectively.

[0080] Step 5-2: Based on the mass of each mesh element in the simplified model of the wing tooling flag, calculate the total mass m of the entire simplified tooling flag model as follows:

[0081]

[0082] in, Let be the mass of the i-th mesh element in the simplified model of the wing tooling flag, and n be the total number of mesh elements in the simplified model of the wing tooling flag.

[0083] Step 5-3: Using a statistical algorithm, the maximum value in the displacement matrix [U] of the simplified model of the wing tooling flag is obtained as the stiffness index of the simplified model of the tooling flag, and the mass of the tooling flag is used as the weight index of the tooling flag.

[0084] In one implementation of this invention, step six above, which involves establishing a quantitative design method for the stiffness of the tooling flag, includes the following steps:

[0085] Step 6-1: List the structural parameters that need to be designed for the simplified model of the wing tooling flag and their value ranges, including the length, width, height, material type, and tooling flag rib form of the simplified model of the wing tooling flag.

[0086] Step 6-2: Take all structural parameters to be designed and their value ranges as input conditions, repeat steps 5-1 to 5-3, and calculate the tooling stiffness index and weight index corresponding to each structural parameter design combination in turn.

[0087] Step 6-3: Based on the calculation results in Step 6-2, select the minimum weight that meets the stiffness index requirements of the tooling flag as the optimal tooling flag design scheme before designing the tooling flag.

[0088] Based on efficient simulation technology, this invention provides a quantitative design method for the stiffness of wing tooling flags. Considering factors such as the flag's form, geometry, material, weight, and the location and magnitude of external loads, a simplified model of the tooling flag is established. Efficient simulation calculations are then performed, calculating every structural parameter required in the flag design before the formal design phase. Post-processing is then performed on the mesh data of the simplified model, and the optimal parameter scheme is selected based on the calculated structural parameters. This reduces the flag's weight while ensuring its stiffness, preventing structural deformation due to insufficient stiffness. The quantitative design method for the stiffness of wing tooling flags provided by this invention offers a theoretical basis for optimized design and is a fast and effective design method.

[0089] Based on the method for quantitative stiffness design of wing tooling flags provided in the above embodiments of the present invention, the present invention also provides a computer-readable storage medium, including: a memory and a processor.

[0090] The memory is used to store computer-readable programs;

[0091] The processor is configured to implement, when executing a computer-readable program, a method for quantitative stiffness design of wing tooling flags as provided in any of the above embodiments.

[0092] The following is an illustrative example illustrating the implementation of the method for quantitative stiffness design of wing tooling flags provided by the present invention.

[0093] Implementation Example

[0094] like Figure 1 As shown, the implementation example provides a method for quantitative design of stiffness for wing tooling flags, which is carried out through the following steps:

[0095] Step 1: Establish a three-dimensional geometric model of the tooling flag, and obtain a simplified model of the wing tooling flag by simplifying the three-dimensional geometric model.

[0096] Step 2: Set mechanical boundary conditions for the simplified model of the wing tooling flag;

[0097] Step 3: Based on the simplified model of the wing tooling flag and the location of the load application points in the model, establish constraint equations;

[0098] Step 4: By applying a concentrated load to the load application point based on the simplified tooling flag model, the displacement field results of the simplified wing tooling flag model under the concentrated load are obtained.

[0099] Step 5 involves meshing the simplified model of the tooling flag and post-processing the mesh cells, including: using the displacement field results obtained in Step 4 and the mesh cells divided from the simplified model of the wing tooling flag, to obtain the displacement matrix and total mass of the simplified model of the wing tooling flag.

[0100] Step six: By combining the structural parameters in the simplified model of the wing tooling flag, the optimal tooling flag design scheme that meets the stiffness index requirements is calculated using the calculation method in step five.

[0101] In this implementation example, the specific process for establishing a reasonably simplified finite element model of the tooling flag in step one above is as follows:

[0102] Step 1-1: Use CATIA V5 2018 software to create a three-dimensional geometric model of the wing tooling flag. In this model, all parts except bolts and gaskets are deleted to create a simplified model of the wing tooling flag.

[0103] This step requires ensuring that the simplified model of the wing tooling flag has the same length, width, and height dimensions as the original wing tooling flag, and that the positions of the tooling flag end plate 2, tooling flag rib 3, tooling flag front face 4, and bolt holes 5 in the simplified model are consistent with the actual wing tooling flag 1. Figure 2 The figure shown is a schematic diagram of the finite element model of the wing tooling flag in the quantitative design method for stiffness of the wing tooling flag provided in an embodiment of the present invention.

[0104] Step 1-2: Establish a load application point at the center of the end face in the simplified model of the wing tooling flag. In this implementation example, the coordinates of the load application point are (0, 300, 480). Apply the concentrated load of 150N on the tooling flag to this load application point.

[0105] In this implementation example, the implementation method for the finite element simulation calculation of the tooling flag in step two above may include the following steps:

[0106] Step 2-1: Based on the material type of the wing tooling flag, set the Young's modulus and Poisson's ratio of the actual wing tooling flag to 210 GPa and 0.30 respectively, and take the material density as 7.8 × 10⁻⁹ t / mm². 3 .

[0107] Step 2-2: Constrain the bolt hole positions in the simplified wing tooling model with 6 degrees of freedom as the mechanical boundary conditions of the simplified wing tooling model.

[0108] In this implementation example, step three above is implemented as follows: Based on the load application point location in the simplified model of the wing tooling flag, constraint equations are established for the simplified model of the wing tooling flag at the load application point and the leading edge of the tooling flag as follows:

[0109]

[0110] Where u1, u2, and u3 represent the three displacement components in the heading, span, and gravity directions of the aircraft, respectively; the superscripts F and w represent the tooling flag and the load application point, respectively; λ is the set value of the periodic boundary condition, and considering that there is a rigid constraint between the tooling flag and the load application point, λ = 0 is taken.

[0111] In this implementation example, step four above is implemented through the following steps:

[0112] Step 4-1: Mesh the simplified model of the wing tooling flag: The maximum dimensions of the mesh element 6 in the simplified model of the wing tooling flag should not exceed 10% of the length, width, and height of the wing tooling flag. Figure 3 The diagram shown is a schematic of the finite element mesh model in the quantitative stiffness design method for wing tooling flags provided in an embodiment of the present invention.

[0113] Step 4-2: In the ABAQUS 6.13 finite element software, apply a concentrated load of 150N to the load application point of the simplified model of the wing tooling flag, and solve the displacement and stress fields of the wing tooling flag under the concentrated load using the statics module.

[0114] In this implementation, the post-processing of the grid cell data in step five above includes the following steps:

[0115] Step 5-1: Number each mesh cell in the tooling flag model according to the formula.

[0116] Equation 2 stores the displacement components u1, u2, and u3 corresponding to the numbers into matrix [U].

[0117]

[0118] The first column lists the mesh element numbers from 1 to n in the simplified model of the wing tooling flag; the second to fourth columns list the displacement components corresponding to the mesh element numbers, where u i,1 u i,2 u i,3 These represent the displacement components of the i-th grid cell in the heading, span, and gravity directions, respectively.

[0119] Step 5-2: Based on the mass of each mesh element in the simplified model of the wing tooling flag, calculate the total mass m of the entire simplified tooling flag model as follows:

[0120]

[0121] in, Let be the mass of the i-th grid cell in the model, and n be the total number of grid cells in the model.

[0122] In this implementation example, n = 12631 is set, and m = 65.2 kg is calculated.

[0123] Step 5-3: Using a statistical algorithm, the maximum value in the displacement matrix [U] of the simplified model of the wing tooling flag is obtained as the stiffness index of the simplified model of the tooling flag, and the mass of the tooling flag is used as the weight index of the tooling flag.

[0124] In this implementation example, the stiffness index is 0.09 mm, and the calculated weight index is 65.2 kg.

[0125] In this implementation example, step six above, which establishes the quantitative design method for the stiffness of the tooling flag, includes the following steps:

[0126] Step 6-1: List the structural parameters that need to be designed for the tooling flag and their value ranges, including the length, width, height, material, and rib type of the tooling flag.

[0127] In this implementation example, the width of the work flag ranges from 32mm to 48mm, and the materials used are steel and aluminum alloy, respectively. The rib width is 10mm and the height is 10mm.

[0128] Step 6-2: Using all structural parameters and their value ranges as input conditions, repeat steps 5-1 to 5-3 to calculate the tooling stiffness index, tooling weight index, and tooling mass for each design combination. Figure 4 and Figure 5 As shown; Figure 4 This is a schematic diagram showing the mass of the tooling flag calculated under different design widths in the quantitative design method for stiffness of the tooling flag for an airfoil provided in an embodiment of the present invention. Figure 5 This is a schematic diagram showing the displacement of the tooling flag under different materials, calculated in the quantitative design method for stiffness of the tooling flag for the wing provided in the embodiments of the present invention.

[0129] Step 6-3: Based on the calculation results in Step 6-2, the tooling design selects the structural parameters and their values ​​that meet the index requirements as the tooling design scheme.

[0130] While the embodiments disclosed in this invention are as described above, they are merely illustrative of the embodiments to facilitate understanding of the invention and are not intended to limit the invention. Any person skilled in the art to which this invention pertains may make any modifications and variations in the form and details of the implementation without departing from the spirit and scope disclosed herein; however, the scope of patent protection for this invention shall still be determined by the scope defined in the appended claims.

Claims

1. A method for quantitatively designing the stiffness of a tooling flag for an aircraft wing, characterized in that, include: Step 1: Establish a three-dimensional geometric model of the tooling flag, and obtain a simplified model of the wing tooling flag by simplifying the three-dimensional geometric model. Step 2: Set mechanical boundary conditions for the simplified model of the wing tooling flag; Step 3: Based on the simplified model of the wing tooling flag and the location of the load application points in the model, establish constraint equations; Step 4: By applying a concentrated load to the load application point based on the simplified tooling flag model, the displacement field results of the simplified wing tooling flag model under the concentrated load are obtained. Step 5 involves meshing the simplified model of the tooling flag and post-processing the mesh cells, including: using the displacement field results obtained in Step 4 and the mesh cells divided from the simplified model of the wing tooling flag, to obtain the displacement matrix and total mass of the simplified model of the wing tooling flag. Step six: By combining the structural parameters in the simplified model of the wing tooling flag, the optimal tooling flag design scheme that meets the stiffness index requirements is calculated using the calculation method in step five. Step three includes: Based on the location of the load application point in the simplified model of the wing tooling flag, the constraint equations for the simplified model of the wing tooling flag at the load application point and the leading edge face of the tooling flag are as follows: ； in, , , These represent the three displacement components of the aircraft in the heading, span, and gravity directions, respectively; the superscripts F and w represent the tooling flag and the point of application of the load, respectively. Set values ​​for periodic boundary conditions.

2. The method for quantitative stiffness design of a wing tooling flag according to claim 1, characterized in that, Step one includes: Step 1-1: Use CAD software to create a three-dimensional geometric model of the wing tooling flag. In the three-dimensional geometric model, delete all parts except bolts and gaskets in the wing tooling flag model to obtain a simplified model of the wing tooling flag. Steps 1-2: Set a load application point at the center of the end face in the simplified model of the wing tooling flag; the load application point is used as the load application point of the simplified model of the wing tooling flag in subsequent finite element calculations.

3. The method for quantitative stiffness design of a wing tooling flag according to claim 2, characterized in that, The simplified model of the wing tooling flag obtained in step 1-1 has the following requirements: The simplified model must have the same length, width, and height as the actual wing tooling flag, and the simplified model must have the same end plate, tooling flag rib, tooling flag front face, and bolt hole positions as the actual wing tooling flag.

4. The method for quantitative stiffness design of a wing tooling flag according to claim 2, characterized in that, Step two includes: Step 2-1: Based on the material type in the simplified model of the wing tooling flag, set the Young's modulus, Poisson's ratio, and material density of the actual wing tooling flag. Step 2-2: Set 6-DOF constraints at the bolt hole positions in the simplified model of the wing tooling flag as the mechanical boundary conditions of the simplified model of the wing tooling flag.

5. The method for quantitative stiffness design of a wing tooling flag according to claim 4, characterized in that, Step four includes: Step 4-1: Mesh the simplified model of the wing tooling flag. The maximum dimensions of the mesh elements in the simplified model of the wing tooling flag shall not exceed 10% of the length, width, and height of the wing tooling flag. Step 4-2: Input the mechanical boundary conditions and constraint equations into the finite element software, apply a concentrated load to the load application point of the simplified model of the wing tooling flag, and solve it using the statics method to obtain the displacement field results of the simplified model of the wing tooling flag under the concentrated load.

6. The method for quantitative stiffness design of a wing tooling flag according to claim 5, characterized in that, Step five includes: Step 5-1: Number each mesh element in the simplified model of the wing tooling flag. Based on the calculation results in Step 4, store the displacement components corresponding to each mesh element number into the displacement matrix. In the middle, we get: ； The first column represents the mesh element numbers from 1 to n in the simplified model of the wing tooling flag; the second to fourth columns represent the displacement components corresponding to the mesh element numbers. u i,1 、u i,2 、u i,3 They represent the first i Displacement components of each grid cell in the heading, span, and gravity directions; Step 5-2: Calculate the total mass of the entire simplified wing tooling flag model based on the mass of each mesh element in the simplified model. for: ； in, The simplified model of the wing tooling flag i The quality of each grid cell n The total number of mesh elements for the simplified model of the wing tooling flag; Step 5-3: Using a statistical algorithm, obtain the displacement matrix of the simplified model of the wing tooling flag. The maximum value in the value is used as the stiffness index of the simplified tooling flag model, and the mass of the tooling flag is used as the weight index of the tooling flag.

7. The method for quantitative stiffness design of a wing tooling flag according to claim 6, characterized in that, Step six establishes a quantitative design method for the stiffness of the tooling flag, including the following steps: Step 6-1: List the structural parameters that need to be designed for the simplified model of the wing tooling flag and their value ranges, including the length, width, height, material type, and tooling flag rib form of the simplified model of the wing tooling flag. Step 6-2: Take all structural parameters to be designed and their value ranges as input conditions, repeat steps 5-1 to 5-3, and calculate the tooling stiffness index and weight index corresponding to each structural parameter design combination in turn. Step 6-3: Based on the calculation results in Step 6-2, select the minimum weight that meets the stiffness index requirements of the tooling flag as the optimal tooling flag design scheme before designing the tooling flag.

8. 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 implement, when executing a computer-readable program, the method for quantitative stiffness design of a wing tooling flag as described in any one of claims 1 to 7.

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