Quantitative design method for rigidity of wing tooling flag

Abstract

The invention discloses a method for quantitatively designing the rigidity of a wing tooling flag, which comprises the following steps of: 1, establishing a three-dimensional geometric model of the tooling flag, and simplifying the three-dimensional geometric model to obtain a simplified model of the wing tooling flag; 2, mechanical boundary conditions are set for the simplified model of the wing tooling flag; step 3, establishing a constraint equation according to the simplified model of the wing tooling flag and the position of a load action point in the model; 4, applying a concentrated load to a load acting point based on the tool flag simplification model, and solving a displacement field result of the wing tool flag simplification model under the concentrated load; 5, carrying out grid division on the tool flag simplified model and carrying out data post-processing on grid units, namely obtaining a displacement matrix and total mass of the wing tool flag simplified model by adopting the displacement field result obtained in the step 4 and the grid units divided by the wing tool flag simplified model; and step 6, calculating an optimal tooling flag design scheme meeting the rigidity index requirement by combining structural parameters in the simplified model of the wing tooling flag and adopting the calculation mode in the step 5. According to the technical scheme, the optimal parameter scheme is selected in the design according to the calculation result, the weight of the tool flag is reduced on the premise that the rigidity of the tool flag is guaranteed, structural deformation caused by insufficient rigidity of the tool flag is avoided, the proposed rigidity quantitative design method can provide a theoretical basis for optimization design, and the method is suitable for popularization and application. The method is a rapid and effective design method.

Description

Technical Field

[0001] The invention relates to the field of tooling design technology, but is not limited to it, and in particular to a method for quantitatively designing the stiffness of a wing tooling flag. Background Art

[0002] In order to complete the wing assembly with high quality, the wing assembly tool is usually equipped with a tooling flag. The tooling flag is used to connect the wing intersection and the tooling body, which directly affects the assembly accuracy and stability. In order to prevent the tooling flag structure from deforming during use, which leads to a decrease in assembly accuracy, the structure of the tooling flag needs to be optimized.

[0003] At present, the traditional design method of tooling flags is determined by manual experience. Due to the lack of mathematical relationship between design parameters and structural stiffness, the rigidity of the tooling flag is usually increased by increasing the end cross-sectional area of ​​the tooling flag and selecting higher strength materials, thereby increasing the weight of the entire tooling flag and increasing manufacturing costs. It may also cause the tooling flag to be too rigid, causing uncoordinated deformation of the entire assembly system. Summary of the invention

[0004] Purpose of the present invention: In order to solve the above-mentioned technical problems, an embodiment of the present invention provides a method for quantitatively designing the stiffness of a wing tooling flag, so as to solve the existing design method of the tooling flag. Since the rigidity of the tooling flag is increased by increasing the end cross-sectional area of ​​the tooling flag, selecting a higher strength material, etc., the weight of the entire tooling flag is increased, the manufacturing cost is increased, and the tooling flag may be too rigid, thereby causing problems such as uncoordinated deformation of the entire assembly system.

[0005] Technical solution of the present invention: In a first aspect, an embodiment of the present invention provides a method for quantitatively designing stiffness of a wing tooling flag, comprising:

[0006] Step 1, establishing a three-dimensional geometric model of the tooling flag, and obtaining a simplified model of the wing tooling flag by simplifying the three-dimensional geometric model;

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

[0008] Step 3, establishing constraint equations according to the simplified model of the wing tooling flag and the position of the load action point in the model;

[0009] Step 4, by applying a concentrated load at the load action point based on the simplified model of the tooling flag, the displacement field result of the simplified model of the wing tooling flag under the concentrated load is solved;

[0010] Step 5, meshing the simplified model of the wing tooling flag and post-processing the data of the mesh units, including: using the displacement field result obtained in step 4 and the mesh units divided by 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, using the calculation method of step five, calculate the best tooling flag design that meets the stiffness index requirements.

[0012] Optionally, in the above-mentioned method for quantitatively designing the stiffness of a wing tooling flag, the step 1 comprises:

[0013] Step 1-1, using CAD software to establish a three-dimensional geometric model of the wing tooling flag, and obtaining a simplified model of the wing tooling flag by deleting all parts except bolts and gaskets in the three-dimensional geometric model;

[0014] Step 1-2, setting a load application point at the center position of the end surface 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 above-mentioned method for quantitative stiffness design of a wing tooling flag, the simplified model of the wing tooling flag obtained in step 1-1 has the following requirements:

[0016] The simplified model is required to have the same length, width and height as the actual wing tooling flag, and the tooling flag end plate, tooling flag ribs, tooling flag front end face and bolt hole positions in the simplified model are required to be consistent with the actual wing tooling flag.

[0017] Optionally, in the above-mentioned method for quantitatively designing the stiffness of a wing tooling flag, the step 2 comprises:

[0018] Step 2-1, according to 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 a 6-DOF constraint at the bolt hole position in the simplified model of the wing tooling flag as the mechanical boundary condition of the simplified model of the wing tooling flag.

[0020] Optionally, in the above-mentioned method for quantitatively designing the stiffness of a wing tooling flag, the step three comprises:

[0021] Based on the position of the load action 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 action point and the front end of the tooling flag are established as follows:

[0022]

[0023] Among them, 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 setting value of the periodic boundary condition.

[0024] Optionally, in the above-mentioned method for quantitatively designing the stiffness of a wing tooling flag, the step 4 comprises:

[0025] Step 4-1, dividing the simplified model of the wing tooling flag into grid units, wherein the maximum length, width and height of the grid units 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 in the finite element software, apply concentrated loads on the load application points of the simplified model of the wing tooling flag, and solve it using the static mechanics solution method to calculate the displacement field results of the simplified model of the wing tooling flag under the concentrated load.

[0027] Optionally, in the above-mentioned method for quantitatively designing stiffness of a wing tooling flag, the step five comprises:

[0028] Step 5-1, number each grid unit in the simplified model of the wing tooling flag, and according to the calculation result of step 4, store the displacement component corresponding to each grid unit number into the displacement matrix [U] to obtain:

[0029]

[0030] The first column is the number of grid cells 1 to n in the simplified model of the wing tooling flag; the second to fourth columns are the displacement components corresponding to the grid cell numbers, where u i,1 、u i,2 、u i,3 Respectively represent the displacement components of the i-th grid unit in the heading, span, and gravity directions;

[0031] Step 5-2, according to the mass of each grid unit in the simplified model of the wing tooling flag, the total mass m of the simplified model of the entire tooling flag is calculated as:

[0032]

[0033] in, is the mass of the i-th grid unit in the simplified model of the wing tooling flag, and n is the total number of grid units in the simplified model of the wing tooling flag;

[0034] Step 5-3, using a statistical algorithm, obtain the maximum value in the displacement matrix [U] of the simplified model of the wing tooling flag as the stiffness index of the simplified model of the tooling flag, and use the mass of the tooling flag as the weight index of the tooling flag.

[0035] Optionally, in the above-mentioned method for quantitative stiffness design of a wing tooling flag, step six of establishing a quantitative stiffness design method of a tooling flag comprises the following steps:

[0036] Step 6-1, list the structural parameters and value ranges that need to be designed for the simplified model of the wing tooling flag, 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, taking all the structural parameters to be designed and their value ranges as input conditions, repeating steps 5-1 to 5-3, and calculating the stiffness index and weight index of the tooling flag corresponding to each structural parameter design combination in turn;

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

[0039] In a second aspect, an embodiment of the present invention further provides a computer-readable storage medium, including: a memory and a processor;

[0040] Wherein, the memory is used to store a computer-readable program;

[0041] The processor is used to implement the stiffness quantitative design method for a wing tooling flag as described in any one of the above items when executing a computer-readable program.

[0042] Beneficial effects of the present invention: Based on efficient simulation technology, an embodiment of the present invention provides a method for quantitatively designing the stiffness of wing tooling flags. Based on the consideration of factors such as the tooling flag form, tooling flag geometric dimensions, tooling flag materials, tooling flag weight, external load action location and load size, a reasonably simplified tooling flag simplified model is established to carry out efficient simulation calculations, that is, each structural parameter that needs to be designed in the tooling flag design is calculated before the formal design; post-processing is performed on the grid unit data of the established tooling flag simplified model, and the optimal parameter scheme is selected in the design according to the calculation results of the tooling flag structural parameters, so as to reduce the weight of the tooling flag under the premise of ensuring the stiffness of the tooling flag, and avoid structural deformation caused by insufficient stiffness of the tooling flag. The method for quantitatively designing the stiffness of the wing tooling flag provided by the embodiment of the present invention can provide a theoretical basis for optimizing the design, and is a fast and effective design method. BRIEF DESCRIPTION OF THE DRAWINGS

[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 A flowchart of a method for quantitatively designing stiffness of a wing tooling flag proposed by the present invention;

[0045] Figure 2 A schematic diagram of a finite element model of a wing tooling flag used in a method for quantitatively designing stiffness of a wing tooling flag provided in an embodiment of the present invention;

[0046] Figure 3 A schematic diagram of a mesh unit model of a finite element used in a method for quantitatively designing stiffness of a wing tooling flag provided in an embodiment of the present invention;

[0047] Figure 4 A schematic diagram of the mass of a wing tooling flag at different design widths calculated in the method for quantitatively designing the stiffness of the wing tooling flag provided in an embodiment of the present invention;

[0048] Figure 5 A schematic diagram of the tooling flag displacements of different materials calculated in the stiffness quantitative design method for a wing tooling flag provided in an embodiment of the present invention.

[0049] Description of reference numerals:

[0050] 1. Wing tooling flag; 2. Tooling flag end plate; 3. Tooling flag rib; 4. Tooling flag front end face; 5. Bolt hole; 6. Grid unit. DETAILED DESCRIPTION

[0051] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be noted that the embodiments and features in the embodiments of the present application can be combined with each other arbitrarily without conflict.

[0052] The above background technology has explained the important role of wing tooling flags in wing assembly and the necessity of designing the wing tooling flag structure. In view of the many problems existing in the existing design methods of tooling flags, an embodiment of the present invention provides a stiffness quantitative design method for wing tooling flags, specifically, a tooling flag design method that combines the efficient calculation results of the tooling flag stiffness.

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

[0054] Figure 1The flowchart of the stiffness quantitative design method for a wing tooling flag proposed by the present invention. The stiffness quantitative design method for a wing tooling flag provided by an embodiment of the present invention comprises the following steps:

[0055] Step 1, establishing a three-dimensional geometric model of the tooling flag, and obtaining a simplified model of the wing tooling flag by simplifying the three-dimensional geometric model;

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

[0057] Step 3, establishing constraint equations according to the simplified model of the wing tooling flag and the position of the load action point in the model;

[0058] Step 4, by applying a concentrated load at the load action point based on the simplified model of the tooling flag, the displacement field result of the simplified model of the wing tooling flag under the concentrated load is solved;

[0059] Step 5, meshing the simplified model of the wing tooling flag and post-processing the data of the mesh units, including: using the displacement field result obtained in step 4 and the mesh units divided by 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, using the calculation method of step five, calculate the best tooling flag design that meets the stiffness index requirements.

[0061] In one implementation of the embodiment of the present invention, the implementation process of the above step 1 may include:

[0062] Step 1-1, using CAD software to establish a three-dimensional geometric model of the wing tooling flag, and obtaining a simplified model of the wing tooling flag by deleting all parts except bolts and gaskets in the three-dimensional geometric model;

[0063] Step 1-2, setting a load application point at the center position of the end surface 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 implementation, the simplified model of the wing tooling flag is obtained in step 1-1, which has the following requirements:

[0065] The simplified model is required to have the same length, width and height as the actual wing tooling flag, and the tooling flag end plate, tooling flag ribs, tooling flag front end face and bolt hole positions in the simplified model are required to be consistent with the actual wing tooling flag.

[0066] In one implementation of the embodiment of the present invention, the implementation process of the above step 2 may include:

[0067] Step 2-1, according to 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 a 6-DOF constraint at the bolt hole position in the simplified model of the wing tooling flag as the mechanical boundary condition of the simplified model of the wing tooling flag.

[0069] In one implementation of the embodiment of the present invention, the implementation process of the above step three may include:

[0070] Based on the position of the load action 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 action point and the front end of the tooling flag are established as follows:

[0071]

[0072] Among them, 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 setting value of the periodic boundary condition.

[0073] In one implementation of the embodiment of the present invention, the implementation process of the above step 4 may include:

[0074] Step 4-1, dividing the simplified model of the wing tooling flag into grid units, wherein the maximum length, width and height of the grid units 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 in the finite element software, apply concentrated loads on the load application points of the simplified model of the wing tooling flag, and solve it using the static mechanics solution method to calculate the displacement field results of the simplified model of the wing tooling flag under the concentrated load.

[0076] In one implementation of the embodiment of the present invention, the implementation process of the above step 5 may include:

[0077] Step 5-1, number each grid unit in the simplified model of the wing tooling flag, and according to the calculation result of step 4, store the displacement component corresponding to each grid unit number into the displacement matrix [U] to obtain:

[0078]

[0079] The first column is the number of grid cells 1 to n in the simplified model of the wing tooling flag; the second to fourth columns are the displacement components corresponding to the grid cell numbers, where u i,1 、u i,2 、u i,3Respectively represent the displacement components of the i-th grid unit in the heading, span, and gravity directions;

[0080] Step 5-2, according to the mass of each grid unit in the simplified model of the wing tooling flag, the total mass m of the simplified model of the entire tooling flag is calculated as:

[0081]

[0082] in, is the mass of the i-th grid unit in the simplified model of the wing tooling flag, and n is the total number of grid units in the simplified model of the wing tooling flag.

[0083] Step 5-3, using a statistical algorithm, obtain the maximum value in the displacement matrix [U] of the simplified model of the wing tooling flag as the stiffness index of the simplified model of the tooling flag, and use the mass of the tooling flag as the weight index of the tooling flag.

[0084] In one implementation of the embodiment of the present invention, the method for establishing the stiffness quantitative design of the tooling flag in step 6 above includes the following steps:

[0085] Step 6-1, list the structural parameters and value ranges that need to be designed for the simplified model of the wing tooling flag, 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, taking all the structural parameters to be designed and their value ranges as input conditions, repeating steps 5-1 to 5-3, and calculating the stiffness index and weight index of the tooling flag corresponding to each structural parameter design combination in turn;

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

[0088] Based on efficient simulation technology, an embodiment of the present invention provides a method for quantitatively designing the stiffness of wing tooling flags. Based on the consideration of factors such as the tooling flag form, tooling flag geometric dimensions, tooling flag materials, tooling flag weight, external load action location and load size, a reasonably simplified tooling flag simplified model is established to carry out efficient simulation calculations, that is, each structural parameter that needs to be designed in the tooling flag design is calculated before the formal design; post-processing is performed on the grid unit data of the established tooling flag simplified model, and the optimal parameter scheme is selected in the design according to the calculation results of the tooling flag structural parameters, so as to reduce the weight of the tooling flag under the premise of ensuring the stiffness of the tooling flag, and avoid structural deformation caused by insufficient stiffness of the tooling flag. The method for quantitatively designing the stiffness of the wing tooling flag provided by the embodiment of the present invention can provide a theoretical basis for optimized design, and is a fast and effective design method.

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

[0090] Wherein, the memory is used to store a computer-readable program;

[0091] The processor is used to implement the stiffness quantitative design method for the wing tooling flag provided in any one of the above embodiments when executing the computer readable program.

[0092] The following is a schematic illustration of an implementation example of the method for quantitatively designing the stiffness of a wing tooling flag provided by an embodiment of the present invention.

[0093] Implementation Example

[0094] like Figure 1 As shown, the implementation example provides a method for quantitatively designing the stiffness of a wing tooling flag through the following steps:

[0095] Step 1, establishing a three-dimensional geometric model of the tooling flag, and obtaining a simplified model of the wing tooling flag by simplifying the three-dimensional geometric model;

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

[0097] Step 3, establishing constraint equations according to the simplified model of the wing tooling flag and the position of the load action point in the model;

[0098] Step 4, by applying a concentrated load at the load action point based on the simplified model of the tooling flag, the displacement field result of the simplified model of the wing tooling flag under the concentrated load is solved;

[0099] Step 5, meshing the simplified model of the wing tooling flag and post-processing the data of the mesh units, including: using the displacement field result obtained in step 4 and the mesh units divided by 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, using the calculation method of step five, calculate the best tooling flag design that meets the stiffness index requirements.

[0101] In this implementation example, the implementation method of establishing a reasonably simplified finite element model of the tooling flag in the above step 1 is as follows:

[0102] Step 1-1, using CATIA V5 2018 software to establish a three-dimensional geometric model of the wing tooling flag, wherein all parts except bolts and washers in the wing tooling flag model are deleted as a simplified model of the wing tooling flag;

[0103] In this step, it is required to ensure that the simplified model of the wing tooling flag has the same length, width and height as the original wing tooling flag, and the positions of the tooling flag end plate 2, tooling flag rib 3, tooling flag front end face 4 and bolt hole 5 in the simplified model of the wing tooling flag are consistent with those of the wing tooling flag 1. Figure 2 , which is a schematic diagram of a finite element model of a wing tooling flag used in a method for quantitatively designing stiffness of a 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 surface in the simplified model of the wing tooling flag. The coordinates of the load application point in this implementation example are (0, 300, 480), and the concentrated load of 150N on the tooling flag is applied to the load application point.

[0105] In this implementation example, the implementation method of the finite element simulation calculation of the tooling flag in the above step 2 may include the following steps:

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

[0107] Step 2-2, constrain 6 degrees of freedom in the bolt hole position in the simplified model of the wing tooling as the mechanical boundary conditions of the simplified model of the wing tooling.

[0108] In this implementation example, the implementation method of the above step three is: based on the position of the load action point in the simplified model of the wing tooling flag, the constraint equation is established for the simplified model of the wing tooling flag at the load action point and the front end surface of the tooling flag as follows:

[0109]

[0110] Among them, u1, u2, and u3 represent the three displacement components of the aircraft heading, span direction, and gravity direction, respectively; the superscripts F and w represent the tooling flag and the load application point, respectively; λ is the setting value of the periodic boundary condition. Considering that there is a rigid constraint between the tooling flag and the load application point, λ=0.

[0111] In this implementation example, the implementation of step 4 above is achieved through the following steps:

[0112] Step 4-1, divide the simplified model of the wing tooling flag into grid units: the maximum length, width and height of the grid unit 6 in the simplified model of the wing tooling flag shall not exceed 10% of the length, width and height of the wing tooling flag, such as Figure 3 , which is a schematic diagram of a finite element mesh unit model used in a stiffness quantitative design method for a wing tooling flag provided in an embodiment of the present invention.

[0113] Step 4-2, in ABAQUS 6.13 finite element software, apply a concentrated load of 150N to the load action point of the simplified model of the wing tooling flag, and solve it through the statics module to calculate the displacement field and stress field results of the wing tooling flag under the concentrated load.

[0114] In this implementation, the post-processing of the grid unit data in the above step 5 includes the following steps:

[0115] Step 5-1: Number each grid unit in the tooling flag model according to the

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

[0117]

[0118] The first column is the number of grid cells 1 to n in the simplified model of the wing tooling flag; the second to fourth columns are the displacement components corresponding to the grid cell numbers, where u i,1 、u i,2 、u i,3 They represent the displacement components of the i-th grid unit in the heading, span and gravity directions respectively.

[0119] Step 5-2, according to the mass of each grid unit in the simplified model of the wing tooling flag, the total mass m of the simplified model of the entire tooling flag is calculated as:

[0120]

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

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

[0123] Step 5-3, using a statistical algorithm, obtain the maximum value in the displacement matrix [U] of the simplified model of the wing tooling flag as the stiffness index of the simplified model of the tooling flag, and use the mass of the tooling flag 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, the method for establishing the stiffness quantitative design of the tooling flag in step 6 above 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 form of the tooling flag;

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

[0128] Step 6-2, take all structural parameters and their value ranges as input conditions, repeat steps 5-1 to 5-3, and successively calculate the tooling flag stiffness index, tooling flag weight index, and tooling flag mass obtained in each design combination, such as Figure 4 and Figure 5 As shown; Figure 4 A schematic diagram of the mass of a wing tooling flag at different design widths calculated in the method for quantitatively designing the stiffness of the wing tooling flag provided in an embodiment of the present invention; Figure 5 A schematic diagram of the tooling flag displacements of different materials calculated in the stiffness quantitative design method for a wing tooling flag provided in an embodiment 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 flag design scheme.

[0130] Although the embodiments disclosed in the present invention are as above, the contents are only embodiments adopted to facilitate understanding of the present invention and are not intended to limit the present invention. Any technician in the field to which the present invention belongs can make any modifications and changes in the form and details of implementation without departing from the spirit and scope disclosed in the present invention, but the patent protection scope of the present invention shall still be subject to the scope defined in the attached claims.

Claims

1. A method for quantitatively designing the stiffness of a wing tooling flag, characterized in that: include: Step 1, establishing a three-dimensional geometric model of the tooling flag, and obtaining a simplified model of the wing tooling flag by simplifying the three-dimensional geometric model; Step 2, setting mechanical boundary conditions for the simplified model of the wing tooling flag; Step 3, establishing constraint equations according to the simplified model of the wing tooling flag and the position of the load action point in the model; Step 4, by applying a concentrated load at the load action point based on the simplified model of the tooling flag, the displacement field result of the simplified model of the wing tooling flag under the concentrated load is solved; Step 5, meshing the simplified model of the wing tooling flag and post-processing the data of the mesh units, including: using the displacement field result obtained in step 4 and the mesh units divided by 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, using the calculation method of step five, calculate the best tooling flag design that meets the stiffness index requirements.

2. A method for quantitatively designing the stiffness of a wing tooling flag according to claim 1, characterized in that: The step one comprises: Step 1-1, using CAD software to establish a three-dimensional geometric model of the wing tooling flag, and obtaining a simplified model of the wing tooling flag by deleting all parts except bolts and gaskets in the three-dimensional geometric model; Step 1-2, setting a load application point at the center position of the end surface 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. A method for quantitatively designing the stiffness 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 is required to have the same length, width and height as the actual wing tooling flag, and the tooling flag end plate, tooling flag ribs, tooling flag front end face and bolt hole positions in the simplified model are required to be consistent with the actual wing tooling flag.

4. A method for quantitatively designing the stiffness of a wing tooling flag according to claim 2, characterized in that: The second step comprises: Step 2-1, according to 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 a 6-DOF constraint at the bolt hole position in the simplified model of the wing tooling flag as the mechanical boundary condition of the simplified model of the wing tooling flag.

5. A method for quantitatively designing the stiffness of a wing tooling flag according to claim 4, characterized in that: The step three comprises: Based on the position of the load action 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 action point and the front end of the tooling flag are established as follows: Among them, 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 setting value of the periodic boundary condition.

6. A method for quantitatively designing the stiffness of a wing tooling flag according to claim 5, characterized in that: The fourth step comprises: Step 4-1, dividing the simplified model of the wing tooling flag into grid units, wherein the maximum length, width and height of the grid units 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 in the finite element software, apply concentrated loads on the load application points of the simplified model of the wing tooling flag, and solve it using the static mechanics solution method to calculate the displacement field results of the simplified model of the wing tooling flag under the concentrated load.

7. A method for quantitatively designing the stiffness of a wing tooling flag according to claim 6, characterized in that: The step five comprises: Step 5-1, number each grid unit in the simplified model of the wing tooling flag, and according to the calculation result of step 4, store the displacement component corresponding to each grid unit number into the displacement matrix [U] to obtain: The first column is the number of grid cells 1 to n in the simplified model of the wing tooling flag; the second to fourth columns are the displacement components corresponding to the grid cell numbers, where u i,1 、u i,2 、u i,3 Respectively represent the displacement components of the i-th grid unit in the heading, span, and gravity directions; Step 5-2, according to the mass of each grid unit in the simplified model of the wing tooling flag, calculate the total mass m of the simplified model of the entire tooling flag as: in, is the mass of the i-th grid unit in the simplified model of the wing tooling flag, and n is the total number of grid units in the simplified model of the wing tooling flag; Step 5-3, using a statistical algorithm, obtain the maximum value in the displacement matrix [U] of the simplified model of the wing tooling flag as the stiffness index of the simplified model of the tooling flag, and use the mass of the tooling flag as the weight index of the tooling flag.

8. A method for quantitatively designing the stiffness of a wing tooling flag according to claim 1, characterized in that: Step 6: Establish the stiffness quantitative design method of the tooling flag, including the following steps: Step 6-1, list the structural parameters and value ranges that need to be designed for the simplified model of the wing tooling flag, including the length, width, height, material type, and tooling flag rib form of the simplified model of the wing tooling flag; Step 6-2, taking all the structural parameters to be designed and their value ranges as input conditions, repeating steps 5-1 to 5-3, and calculating the stiffness index and weight index of the tooling flag corresponding to each structural parameter design combination in turn; Step 6-3, based on the calculation results in step 6-2, before designing the tooling flag, select the minimum weight that meets the tooling flag stiffness index requirements as the optimal tooling flag design solution.

9. A computer-readable storage medium, characterized in that: include: Memory and processor; Wherein, the memory is used to store a computer-readable program; The processor is used to implement the stiffness quantitative design method for a wing tooling flag as described in any one of claims 1 to 8 when executing a computer-readable program.

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