Equivalent calculation method for anisotropic rigidity of aviation plate-fin heat exchanger core
The anisotropic stiffness of the core of the aerospace plate-fin heat exchanger was calculated by finite element model. The single array element segmentation method was adopted to solve the complexity of the core structure and the cross-scale problem, realize early dynamic design analysis, and reduce the risk of product failure.
Patent Information
- Application Number
- CN202511470047.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-10-15
- Publication Date
- 2026-02-06
AI Technical Summary
Existing technologies are unable to effectively address the complexity and multi-scale issues of the core structure of aero-plate-fin heat exchangers, leading to difficulties in dynamic design calculations, which in turn affects product vibration testing and structural failures during aircraft operation.
The single array element segmentation method is adopted to calculate the orthogonal anisotropic stiffness parameters of the core structure, including tensile and shear stiffness, through the finite element model, and establish an equivalent stiffness model, which is applicable to fin types such as triangular wave and rectangular straight-through wave.
It enables dynamic calculations of complex multi-scale core structures, solves the problems of early design analysis, and reduces the risk of product failure in vibration tests.
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Figure CN121479923A_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of aerospace equipment calculation and analysis technology, and relates to an equivalent calculation method for anisotropic stiffness of core structures across scales, specifically an equivalent calculation method for anisotropic stiffness of the core of an aerospace plate-fin heat exchanger. Background Technology
[0002] Aircraft plate-fin heat exchangers are one of the important accessory products for aircraft. Due to the harsh mechanical environmental loads such as vibration and shock in aircraft, the structural dynamics design of plate-fin heat exchangers is one of the core contents of their product development. The core of a plate-fin radiator is usually composed of multiple layers of stacked fins and baffles. Common fin types include triangular wave, rectangular straight-through wave, and rectangular sawtooth wave. The fin thickness of aircraft plate-fin radiators is less than 0.5 mm, and the pitch is less than 5 mm, while the total external dimensions of the stacked core are usually several hundred millimeters or more. It is precisely because of the complexity and scale of the core structure that its dynamic design calculations are extremely difficult, making it impossible to carry out dynamic design analysis and evaluation of plate-fin heat exchanger structures in the early stages of the design process. This can easily lead to problems such as product structural failure during vibration testing or aircraft operation.
[0003] Based on the above background analysis, it is necessary to propose an equivalent stiffness calculation method for the anisotropy of plate-fin core structures to solve the problem of design and calculation difficulties caused by the complexity of core structures and their cross-scale nature. Summary of the Invention
[0004] To address the aforementioned issues, this invention proposes an equivalent calculation method for the anisotropic stiffness of a plate-fin heat exchanger core. This method employs a single array element segmentation approach, considering the stiffness characteristics of the upper and lower baffles, and calculates the orthogonal anisotropic equivalent stiffness parameters of the core structure from three tensile and three shear parameters. It is applicable to common fin types such as triangular wave, rectangular straight-through wave, and rectangular sawtooth wave. This method solves the dynamic calculation problem of complex and multi-scale aerospace plate-fin core structures.
[0005] The technical solution of the present invention is as follows: A method for equivalent calculation of anisotropic stiffness of the core structure of an aerospace plate-fin heat exchanger includes the following steps: S1, determine the structural design parameters and material properties of the core and fins of the aerospace plate-fin heat exchanger; S2, the smallest array unit for segmenting and extracting the single-layer core structure; S3, Establish the finite element model of the smallest array element; S4, the normal stiffness of the minimum array element under orthogonal triaxial tensile condition is obtained by calculating the minimum array element finite element model with 3 normal directions; S5, the shear stiffness of the orthogonal triaxial shear condition of the minimum array element is obtained by calculating the minimum array element finite element model with 6 tangential minimum array elements; S6, determine the shape of the smallest array unit and calculate the equivalent parameters of the anisotropic stiffness of the single-layer core structure.
[0006] Furthermore, S1 specifically involves determining the partition thickness, fin thickness, fin waviness, fin pitch, and fin dispersion of the core structure of the aerospace plate-fin heat exchanger, as well as the material data used, including elastic modulus and Poisson's ratio.
[0007] Furthermore, S2 specifically refers to: the fins are array structures, taking 1 / 2 the thickness of the partition plate and the smallest array unit of the fins, with a length direction of 1mm, thereby dividing the smallest array unit of the single-layer core.
[0008] Furthermore, S3 specifically includes the following steps: S31, establish the geometric model of the smallest array element segmented in S2 in the finite element software; S32. Establish a linear elastic material constitutive model based on the elastic modulus and Poisson's ratio of the actual materials of the partition and fins, then create cross-sectional properties and assign the cross-sectional properties to the corresponding geometric model. S33, assemble the geometric model in the finite element software, adjust the coordinate system of the assembly, and ensure that each axis of the global coordinate system is parallel or orthogonal to the geometric model. S34, create a static analysis load step, turn off large deformation; S35, the geometric model is discretized in the mesh generation module; S36, create two reference points in the connection definition module, and establish coupling connection between the two reference points and one side of the partition surface of the minimum array unit; S37, apply constraint boundaries to the smallest array element; S38, repeat steps S36-S37, establish coupling connections between the reference point and the tangential surfaces of other axes respectively, apply constraints and forced displacements, and realize the calculation of working conditions in 3 normal directions and 6 tangential directions in total.
[0009] Furthermore, in S35, a minimum of three mesh layers are required in terms of thickness; in the constraint boundary of S37, the normal degree of freedom is constrained on the cutting surface, one reference point is subject to full degree of freedom constraint, and another reference point is subject to concentrated force load, with the forced displacement directions being one normal and two tangential directions of the partition.
[0010] Furthermore, S4 specifically refers to: By calculating using a finite element model with three normal directions, the displacement components of the reference point where the concentrated force is applied are extracted. The total stiffness of the minimum array element in each direction can be obtained according to the following formula:
[0011] In the formula: The normal total stiffness is in the X direction; The concentrated force is in the X direction; This represents the X-direction deformation component of the reference point under concentrated load.
[0012] Furthermore, S5 specifically refers to: The support reactions at the reference points under forced displacement in their respective tangential directions were calculated using six tangential finite element models. The total stiffness of the minimum array element in each direction can be obtained using the following formula:
[0013] In the formula: The total tangential stiffness in the XY plane; This refers to a concentrated load force in the XY plane. This represents the X-direction deformation component of the reference point under concentrated load.
[0014] Furthermore, S6 specifically includes the following steps: S61, determine the external dimensions of the smallest array unit, and its equivalent model is the solid geometry under that external dimension. Calculate the area of each orthogonal side of the equivalent model. S62, based on the calculation formula of tensile stiffness theory, derive and calculate the anisotropic elastic modulus in the three normal directions; S63: Based on the calculation formula of shear stiffness theory, derive and calculate the anisotropic shear modulus in six tangential directions; S64: Based on the necessary condition for the stability of orthogonal anisotropic constitutive models, three of the six shear moduli are selected as the shear moduli of the final equivalent model. The three normal elastic moduli can be directly used as the material constitutive parameters of the equivalent model to obtain the anisotropic stiffness equivalent parameters of the core structure.
[0015] Furthermore, in S62, the specific calculation formula is as follows:
[0016] In the formula: Let X be the elastic modulus in the X direction of the equivalent model, in MPa; The equivalent model's length in the X direction, in mm; The equivalent model has a cross-sectional area in the YZ plane, in mm. 2 .
[0017] Furthermore, in S63, the specific calculation formula is as follows:
[0018] In the formula: The shear modulus in the XY plane of the equivalent model; The length of the equivalent model in the X direction; This represents the cross-sectional area in the YZ plane of the equivalent model.
[0019] The beneficial effects of this invention are as follows: This invention transforms the complexity of the core structure into an anisotropic stiffness problem through the principle of equivalent transformation. The method uses a single array element segmentation method, considers the stiffness characteristics of the upper and lower partitions, and calculates the orthogonal anisotropic equivalent stiffness parameters of the core structure from three tensions and three shears respectively, thus solving the dynamic calculation problem of complex and multi-scale aerospace plate-fin core structures. Attached Figure Description
[0020] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the embodiments of the present invention will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0021] Figure 1 The flowchart shows the equivalent calculation process for the anisotropic stiffness of the core structure.
[0022] Figure 2 A flowchart for creating a finite element model.
[0023] Figure 3 This is a schematic diagram of the adjacent core structure of a plate-fin heat exchanger.
[0024] Figure 4 This is a planar diagram of the smallest array unit of the triangular wave fin.
[0025] Figure 5 This is the anisotropic constitutive model and stability conditions.
[0026] Table 1. Calculated displacement in each direction.
[0027] Table 2. Total stiffness calculated in each direction.
[0028] Table 3. Anisotropic stiffness parameters calculated in each direction. Detailed Implementation
[0029] This section describes embodiments of the present invention, used to explain and illustrate the technical solutions of the present invention. Unless otherwise specified, the embodiments and features described herein can be combined with each other.
[0030] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating directions or positional relationships, are given in the accompanying drawings and are used only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or device referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include more than one of those features. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.
[0031] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integrated connections; they can refer to mechanical connections or point connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.
[0032] Example 1: An equivalent calculation method for the anisotropic stiffness of the core structure of a pendulum-type aircraft plate-fin heat exchanger is provided, and its implementation steps are as follows: S1: Determine the structural design parameters and related material properties of the core and fins. S2: Divide and extract the smallest array unit of the single-layer core structure. S3: Establish the finite element model of the minimum array element. S4: Calculate the normal stiffness under orthogonal triaxial tension. S5: Calculate the shear stiffness under orthogonal triaxial shear conditions. S6: Calculate the anisotropic stiffness parameters of a single-layer core structure S1 specifically refers to: Determine relevant structural parameters such as baffle thickness, fin thickness, fin waviness, fin pitch or dispersion, as well as material data, including elastic modulus and Poisson's ratio.
[0033] S2 specifically refers to: Plate-fin heat exchanger cores are typically constructed by stacking and brazing multiple layers of cores, with adjacent layers using fin structures to achieve orthogonal flow paths (e.g., ...). Figure 2The single-layer core consists of fins, sealing strips, and upper and lower partitions. The fins are in an array structure. Taking half the partition thickness and the smallest array unit of the fins, with a length of 1mm, the smallest array unit of the single-layer core is divided (e.g., Figure 3 ).
[0034] S3 specifically refers to: S31: Establish the geometric model of the minimum array element segmented in step S1 in the general-purpose finite element software ABAQUS.
[0035] S32: Establish a linear elastic material constitutive model based on the elastic modulus and Poisson's ratio of the actual materials of the partition and fins, then create cross-sectional properties and assign the cross-sectional properties to the corresponding geometric model.
[0036] S33: Assemble the geometric model in ABAQUS software, adjust the coordinate system of the assembly, and ensure that each axis of the global coordinate system is parallel or orthogonal to the geometric model.
[0037] S34: Create a static analysis load step and turn off large deformation.
[0038] S35: Discretize the geometric model in the mesh generation module, requiring at least three mesh layers in thickness.
[0039] S36: Create two reference points in the connection definition module, and establish coupling connections between the two reference points and one side of the partition surface of the minimum array element.
[0040] S37: Apply constraint boundaries to the smallest array element, where the normal degree of freedom on the cutting surface needs to be constrained, one reference point is subject to full degree of freedom constraint, and another reference point is subject to a concentrated force load F=1000N. The directions of the forced displacement are one normal and two tangential directions of the partition.
[0041] By repeating steps S36-S37, the reference point is coupled to the other axial tangential surfaces, and constraints and forced displacements are applied, thus enabling calculations for 3 normal directions and 6 tangential directions.
[0042] S4 specifically refers to: By calculating using a finite element model with three normal directions, the displacement components of the reference point where the concentrated force is applied can be extracted. Then, the total stiffness of the minimum array element in each direction can be obtained according to the following formula:
[0043] In the formula: The normal total stiffness in the X direction is N / mm; The concentrated force in the X direction is 1000 N. The X-direction deformation component of the reference point under concentrated load force is in mm.
[0044] S5 specifically refers to: By calculating the support reaction forces of the reference point in each tangential direction under forced displacement using finite element models in six tangential directions, the total stiffness of the minimum array element in each direction can be obtained according to the following formula:
[0045] In the formula: The total tangential stiffness in the XY plane is expressed in N / mm. The concentrated load force in the XY plane is taken as 1000N; The X-direction deformation component of the reference point under concentrated load force is in mm.
[0046] S6 specifically refers to: S61: Determine the external dimensions (length, width, and height) of the smallest array unit. Its equivalent model is the solid geometry under these external dimensions. Calculate the area of each orthogonal side of the equivalent model.
[0047] S62: Based on the calculation formula of tensile stiffness theory, the anisotropic elastic modulus in the three normal directions is derived and calculated. The specific calculation formula is as follows:
[0048] In the formula: Let X be the elastic modulus in the X direction of the equivalent model, in MPa; The length of the equivalent model in the X direction is in mm; The equivalent model has a cross-sectional area in the YZ plane, in mm. 2 .
[0049] S63: Based on the calculation formula of shear stiffness theory, the anisotropic shear modulus in the six tangential directions is derived and calculated. The specific calculation formula is as follows:
[0050] In the formula: The shear modulus in the XY plane of the equivalent model is expressed in MPa. The length of the equivalent model in the X direction is in mm; The equivalent model has a cross-sectional area in the YZ plane, in mm. 2 .
[0051] S64: According to the necessary condition for the stability of orthogonal anisotropic constitutive structures (such as...) Figure 5 Three of the six shear moduli are selected as the shear moduli of the final equivalent model. The three normal elastic moduli can be directly used as the material constitutive parameters of the equivalent model. Thus, the anisotropic stiffness equivalent parameters of the core structure have been obtained.
[0052] Example 2: An equivalent calculation method for the anisotropic stiffness of the core structure of an aerospace plate-fin heat exchanger is provided, with a specific implementation example as follows: S1 specifically refers to: Taking a rectangular straight-through finned core structure of a certain specification as an example, its relevant structural parameters and material data are determined. The partition thickness t=0.2mm, the fin thickness e=0.1mm, the fin waviness H=3mm, the fin pitch P=1.6mm, and the materials of the fin and the partition are both stainless steel. The elastic modulus E=206GPa and the shear modulus G=79GPa.
[0053] S2 specifically refers to: Take half the thickness of the partition plate and the smallest array unit of the fins, with a length of 1mm, to divide the single-layer core into its smallest array units (e.g., Figure 4 ).
[0054] S3 specifically refers to: S31: Establish the geometric model of the smallest array element segmented in step S1 in the general-purpose finite element software ABAQUS, or create a three-dimensional model using three-dimensional modeling software and then import it into the finite element software ABAQUS. The unit is mm (International System of Units).
[0055] S32: Establish a linear elastic material constitutive model based on the elastic modulus and Poisson's ratio of the actual materials of the partition and fins, then create section properties and assign the section properties to all geometric parts.
[0056] S33: Assemble the geometric model in ABAQUS software, set Instance Type to Independent, and adjust the coordinate system of the assembly to ensure that each axis of the global coordinate system is parallel or orthogonal to the geometric model.
[0057] S34: Create a static analysis load step and turn off large deformation.
[0058] S35: Discretize the geometric model in the mesh generation module. The thickness should be no less than three mesh layers. The overall size should be set to 0.03, and the element type should be C3D8R.
[0059] S36: Create two reference points in the connection definition module. The two reference points are respectively connected to one side of the partition surface of the smallest array element. The coupling type is selected as Kinematic.
[0060] S37: Apply constraint boundaries to the smallest array element, where the normal degree of freedom on the cutting surface needs to be constrained. Apply full degree of freedom constraint to one reference point and apply a concentrated load force of 1000N in the Z direction to the other reference point. Then create two other working cases, only modifying the load direction of the concentrated force applied to the reference point, which are the X and Y directions respectively.
[0061] By repeating steps S36-S37, the reference point is coupled to the other axial tangential surfaces, and constraints and concentrated loads are applied. A total of 3 normal and 6 tangential working conditions are calculated, and the calculation results are shown in Table 1.
[0062] Table 1
[0063] S4 specifically refers to: By calculating using a finite element model with three normal directions, and substituting the displacement components of the reference point from which the concentrated force is applied into the following formula, the total stiffness of the minimum array element in each direction can be obtained:
[0064] In the formula: The normal total stiffness in the X direction is N / mm; The concentrated force in the X direction is 1000 N. The X-direction deformation component of the reference point under concentrated load force is in mm.
[0065] The total stiffness calculation results for the three normal directions are shown in Table 2.
[0066] Table 2
[0067] S5 specifically refers to: By calculating using finite element models in six tangential directions, and substituting the displacement components of the reference point where the concentrated load is applied into the following formula, the total stiffness of the minimum array element in each direction can be obtained:
[0068] In the formula: The total tangential stiffness in the XY plane is expressed in N / mm. The concentrated load force in the XY plane is taken as 1000N; The X-direction deformation component of the reference point under concentrated load force is in mm.
[0069] The total stiffness calculation results for the six normal directions are shown in Table 2.
[0070] S6 specifically refers to: S61: Determine the external dimensions (length, width, and height) of the smallest array unit. Its equivalent model is the solid geometry under these dimensions. Calculate the area of each orthogonal side of the equivalent model (see Table 3).
[0071] S62: Based on the calculation formula of tensile stiffness theory, the anisotropic elastic modulus in the three normal directions is derived and calculated. The specific calculation formula is as follows:
[0072] In the formula: Let X be the elastic modulus in the X direction of the equivalent model, in MPa; The equivalent model's length in the X direction, in mm; The equivalent model has a cross-sectional area in the YZ plane, in mm. 2 .
[0073] S63: Based on the calculation formula of shear stiffness theory, the anisotropic shear modulus in the six tangential directions is derived and calculated. The specific calculation formula is as follows:
[0074] In the formula: The shear modulus in the XY plane of the equivalent model is expressed in MPa. The equivalent model's length in the X direction, in mm; The equivalent model has a cross-sectional area in the YZ plane, in mm. 2 .
[0075] S64: According to the necessary condition for the stability of orthogonal anisotropic constitutive structures (such as...) Figure 5 Three of the six shear moduli are selected as the shear moduli of the final equivalent model. The three normal elastic moduli can be directly used as the material constitutive parameters of the equivalent model. Thus, the anisotropic stiffness equivalent parameters of the core structure have been obtained, as shown in Table 3.
[0076] Table 3
[0077] The above description is merely a specific embodiment of the present invention, providing a detailed description of the invention. Parts not covered herein are conventional techniques. However, the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. The scope of protection of the present invention should be determined by the scope of the claims.
Claims
1. A method for equivalent calculation of anisotropic stiffness of the core of an aerospace plate-fin heat exchanger, characterized in that, Includes the following steps: S1, determine the structural design parameters and material properties of the core and fins of the aerospace plate-fin heat exchanger; S2, the smallest array unit for segmenting and extracting the single-layer core structure; S3, Establish the finite element model of the smallest array element; S4, the normal stiffness of the minimum array element under orthogonal triaxial tensile condition is obtained by calculating the minimum array element finite element model with 3 normal directions; S5, the shear stiffness of the orthogonal triaxial shear condition of the minimum array element is obtained by calculating the minimum array element finite element model with 6 tangential minimum array elements; S6, determine the shape of the smallest array unit and calculate the equivalent parameters of the anisotropic stiffness of the single-layer core structure.
2. The method for equivalent calculation of anisotropic stiffness of the core of an aerospace plate-fin heat exchanger according to claim 1, characterized in that, S1 specifically refers to: determining the partition thickness, fin thickness, fin waviness, fin pitch, and fin dispersion of the core structure of the aerospace plate-fin heat exchanger, as well as the material data used, including elastic modulus and Poisson's ratio.
3. The method for equivalent calculation of anisotropic stiffness of the core of an aerospace plate-fin heat exchanger according to claim 1, characterized in that, S2 specifically refers to: the fins are arrayed, taking 1 / 2 the thickness of the partition plate and the smallest array unit of the fins, with a length direction of 1mm, thereby dividing the smallest array unit of the single-layer core.
4. The method for equivalent calculation of anisotropic stiffness of the core of an aerospace plate-fin heat exchanger according to claim 1, characterized in that, S3 specifically includes the following steps: S31, establish the geometric model of the smallest array element segmented in S2 in the finite element software; S32. Establish a linear elastic material constitutive model based on the elastic modulus and Poisson's ratio of the actual materials of the partition and fins, then create cross-sectional properties and assign the cross-sectional properties to the corresponding geometric model. S33, assemble the geometric model in the finite element software, adjust the coordinate system of the assembly, and ensure that each axis of the global coordinate system is parallel or orthogonal to the geometric model. S34, create a static analysis load step, turn off large deformation; S35, the geometric model is discretized in the mesh generation module; S36, create two reference points in the connection definition module, and establish coupling connection between the two reference points and one side of the partition surface of the minimum array unit; S37, apply constraint boundaries to the smallest array element; S38, repeat steps S36-S37, establish coupling connections between the reference point and the tangential surfaces of other axes respectively, apply constraints and forced displacements, and realize the calculation of working conditions in 3 normal directions and 6 tangential directions in total.
5. The method for equivalent calculation of anisotropic stiffness of the core of an aerospace plate-fin heat exchanger according to claim 4, characterized in that, In S35, a minimum of three mesh layers are required in terms of thickness; in the constrained boundary of S37, the normal degrees of freedom are constrained on the cutting surface, one reference point is subject to full degree of freedom constraint, and another reference point is subject to concentrated force load, with the forced displacement directions being one normal and two tangential directions of the partition.
6. The method for equivalent calculation of anisotropic stiffness of the core of an aerospace plate-fin heat exchanger according to claim 1, characterized in that, S4 specifically refers to: By calculating using a finite element model with three normal directions, the displacement components of the reference point where the concentrated force is applied are extracted. The total stiffness of the minimum array element in each direction can be obtained according to the following formula: In the formula: The normal total stiffness is in the X direction; The concentrated force is in the X direction; This represents the X-direction deformation component of the reference point under concentrated load.
7. The method for equivalent calculation of anisotropic stiffness of the core of an aerospace plate-fin heat exchanger according to claim 1, characterized in that, S5 specifically refers to: The support reactions at the reference points under forced displacement in their respective tangential directions were calculated using six tangential finite element models. The total stiffness of the minimum array element in each direction can be obtained using the following formula: In the formula: The total tangential stiffness in the XY plane; This refers to a concentrated load force in the XY plane. This represents the X-direction deformation component of the reference point under concentrated load.
8. The method for equivalent calculation of anisotropic stiffness of the core of an aerospace plate-fin heat exchanger according to claim 1, characterized in that, S6 specifically includes the following steps: S61, determine the external dimensions of the smallest array unit, and its equivalent model is the solid geometry under that external dimension. Calculate the area of each orthogonal side of the equivalent model. S62, based on the calculation formula of tensile stiffness theory, derive and calculate the anisotropic elastic modulus in the three normal directions; S63: Based on the calculation formula of shear stiffness theory, derive and calculate the anisotropic shear modulus in six tangential directions; S64: Based on the necessary condition for the stability of orthogonal anisotropic constitutive models, three of the six shear moduli are selected as the shear moduli of the final equivalent model. The three normal elastic moduli can be directly used as the material constitutive parameters of the equivalent model to obtain the anisotropic stiffness equivalent parameters of the core structure.
9. The method for equivalent calculation of anisotropic stiffness of the core of an aerospace plate-fin heat exchanger according to claim 8, characterized in that, In S62, the specific calculation formula is as follows: In the formula: The elastic modulus in the X direction of the equivalent model; The length of the equivalent model in the X direction; This represents the cross-sectional area in the YZ plane of the equivalent model.
10. The method for equivalent calculation of anisotropic stiffness of an aerospace plate-fin heat exchanger core according to claim 8, characterized in that, In S63, the specific calculation formula is as follows: In the formula: The shear modulus in the XY plane of the equivalent model; The length of the equivalent model in the X direction; This represents the cross-sectional area in the YZ plane of the equivalent model.