CN112100744B - Laminated plate cluster hole test system - Google Patents
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Abstract
A laminated plate cluster hole test system adopts an improved three-dimensional Hashin failure criterion to explore fiber around a laminated plate hole of a composite material, matrix gradual damage expansion and failure modes from a microscopic angle, and realizes the optimal design of the connecting structure strength of a cluster hole composite material/titanium alloy laminated plate from a structural angle by simulating and analyzing the influence rule of the number of holes and the space layout on the static strength of the connecting structure. The invention realizes the optimal design of the cluster hole strength of the composite material/titanium alloy laminated plate connecting structure from the structural design perspective.
Description
Technical Field
The invention relates to a technology in the field of composite material structures, in particular to a laminated plate cluster hole test system for improving the bearing performance of a carbon fiber composite material and titanium alloy connection structure.
Background
The carbon fiber reinforced resin matrix Composite (CFRP) has a plurality of excellent physical and mechanical properties such as small specific gravity, high strength, good rigidity and the like, and is widely focused and applied in the design and manufacture of large airliners and spacecrafts. Carbon fiber composites are mainly used in wings, tail wings, fuselage and more main load bearing structural members of aircraft, so reinforcing the connection performance of carbon fiber composites is extremely important. At present, the connection methods of the carbon fiber composite material laminated plate are mainly 5, namely mechanical connection, cementing connection, stitching connection, Z-pin connection and mechanical connection/cementing hybrid connection. Because of the shearing, low tensile strength and poor shaping of the carbon fiber composite material, stress concentration occurs around the holes after drilling, so that the connecting structure is easy to damage.
The field of the existing composite material connecting structure is not clear, a unified evaluation system is not clear, the problems of low assembly efficiency of the composite material connecting structure, poor seaworthiness evaluation effect and the like exist, and the feasibility of wide application of the composite material is affected. In the field of composite material plate cluster hole design, how to form a complete cluster hole evaluation system by reasonably designing a layering mode of composite material plates, a connecting mode of laminated plates and the spatial distribution and size of cluster holes in a limited plate size range so as to improve the strength of the composite material plates and the bearing performance of a connecting structure of the laminated plates of the composite material, is a domestic blank and is a work to be researched.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a laminated plate cluster hole test system, wherein a Hashin failure criterion is adopted by establishing a progressive damage model, fiber and matrix progressive damage expansion and failure modes around a laminated plate hole of a composite material are explored from a microscopic angle, the influence rule of the number of holes and space layout on the static strength of a connecting structure is analyzed through simulation, and the optimal design of the cluster hole strength of the connecting structure of the composite material/titanium alloy laminated plate is realized from the structural design angle.
The invention is realized by the following technical scheme:
the invention relates to a strength optimization method of a laminated plate cluster hole connection structure, which comprises the following steps:
step one: and designing a constitutive model of the composite material, a material failure criterion and establishing a three-dimensional composite material/titanium alloy laminated plate model by using finite element simulation software.
The finite element simulation is adopted, but is not limited to ABAQUS or ANSYS, a composite material entity model is built in a composite material module embedded in software, and the composite material entity model and a titanium alloy plate are connected and assembled together through a fastener, so that a three-dimensional composite material/titanium alloy laminated plate model is built.
The constitutive model aims at the anisotropic characteristic of the composite material, and builds the nonlinear constitutive relation of the composite material in the material attribute.
The material failure criterion is obtained by setting a three-dimensional Hashin criterion in finite element simulation as a composite material failure criterion.
Step two: on the basis of the single-hole laminated plate, different connecting modes of the composite material/titanium alloy are replaced, namely, different fastener types are adopted to obtain the influence evaluation of the different fastener types on the laminated plate structure.
The fastener types include bolting and riveting, and when bolting is used, the interference is set in the range of 0-4.5% to achieve the best fit to achieve maximum strength of the connection.
The fastener material is a titanium alloy material widely applied to aviation aircrafts.
Step three: based on the single-hole laminated plate, two different layering modes of single-layering and multi-layering carbon fiber composite materials are adopted to obtain the influence evaluation of different layering angles of the composite materials on the laminated plate structure.
The single-layer refers to: the lay-up of the composite is unidirectional, preferably 0/45/90.
The multi-layering means: the lay-up of the composite is in multiple directions, preferably [90 °,0 °, ±45° ], etc.
Step four: on the basis of the original single-hole connection of the laminated plate, the number of the connecting holes is changed to obtain the number of the connecting holes, and the influence evaluation of the formed graph on the bearing performance of the connecting structure is achieved.
The changing the number of the connecting holes comprises the following steps: 2, 3 or 4 connection holes, wherein:
the 2 connecting holes refer to: the 2 holes must be collinear and the effect of the angle on the connection structure, for example 0/45/90, is analyzed in the case of different angles of variation of the straight line from the direction of the force.
The 3 connecting holes refer to: the 3 holes are collinear or form a triangle, the change in angle being analyzed when collinear, for example 0 °/45 °/90 °; analysis of the effect of side lengths on the connection structure in the case of different side lengths of triangles when forming triangles, for example 40mm/50mm/60mm. In the graphic dimension, assuming that the side length of the triangle is fixed, the effect of the number of holes on the connection structure, e.g. 3 holes/6 holes/9 holes, is analyzed.
The 4 connecting holes refer to: the 4 holes are collinear or square or rhombic/circular, and the change in angle is analyzed when collinear, for example 0/45/90.
When forming a square, the effect of the side length on the connection structure is analyzed in the case of different side lengths of the square, for example 40mm/50mm/60mm. Analysis of the effect of radius on the connection structure in the case of different radii of the diamond/circle, such as R15/R25/R35, was performed when the diamond/circle was composed. In the dimension of the graph, the effect of the number of holes on the connection structure, for example 4 holes/8 holes/12 holes, is analyzed when the side length of the square is fixed. Assuming a constant radius of the circle, the effect of the number of holes on the connection structure is analyzed, e.g. 4 holes/5 holes/6 holes.
Step five: according to the actual connection mode and stress condition of the three-dimensional composite material/titanium alloy laminated plate model, the three-dimensional composite material/titanium alloy laminated plate model is sequentially subjected to finite element simulation software: setting material properties, selecting grid cell types, performing grid division, setting contact properties, and inputting tensile load boundary conditions to obtain a tensile strength simulation result of the composite material/titanium alloy connection structure.
The invention relates to a test system for realizing the method, which comprises the following steps: a composite plate/titanium alloy connection module, fasteners, and clamps for connecting the test pieces to the tensile testing machine.
In order to subject the test sample to uniform tensile load, the upper and lower boundaries of the composite material plate in the composite material plate/titanium alloy connecting module are drilled
The small holes are uniformly distributed.
The position of the composite material plate in the composite material plate/titanium alloy connecting module, which is contacted with the clamp, is reinforced by a metal sheet, the metal sheet is preferably 7075 aluminum alloy material, and the aluminum alloy reinforcing sheet is bonded with the composite material plate by Swiss ergo 1690 acrylic structural adhesive.
The aluminum alloy reinforcing sheet is provided with
The positions of the holes and the centers of the holes coincide with the positions of the holes at the edge of the composite material plate, and the hole diameter is smaller than that of the holes on the composite material plate so as to avoid the composite material plate from being broken at the edge at first.
Technical effects
The invention integrally solves the problems that the existing composite material connecting structure field has not yet defined a uniform evaluation system, and the composite material connecting structure has low assembly efficiency and poor seaworthiness evaluation effect. The tensile strength of the cluster hole composite material/titanium alloy connecting structure is maximized from four dimensions of a connecting mode, a layering mode, the number of holes and a space shape through a strength maximizing scheme.
According to the invention, a progressive damage model is established, an improved three-dimensional Hashin failure criterion is adopted, progressive damage expansion and failure modes of fibers and matrixes around a composite material laminated plate hole are explored from a microscopic angle, the influence rule of the number of holes and the space layout on the static strength of a connecting structure is analyzed through simulation, and the optimal design of the connecting structure strength of the cluster hole composite material/titanium alloy laminated plate is realized from a structural angle.
Drawings
FIG. 1 is a schematic flow chart of the method of the present invention;
FIG. 2 is a flow chart of an embodiment simulation analysis;
FIG. 3 is a schematic diagram of the experimental sample and the stress state when the angle between the hole center connecting line and the stress direction is 0 degrees;
FIG. 4 is a schematic diagram of the experimental sample and the stress state when the hole center connecting line is 45 degrees to the stress direction;
FIG. 5 is a schematic diagram of the experimental sample and the stress state when the hole center connecting line is at an angle of 90 degrees with the stress direction;
in the figure: the device comprises a clamp 1, a composite material laminated plate 2, a titanium alloy plate 3 and an aluminum alloy reinforcing sheet 4;
FIG. 6 is a graph showing the displacement load curve of an experimental sample with a hole center connecting line and a stress direction angle of 0 degrees;
FIG. 7 is a graph showing the displacement load curve of an experimental sample with a 45-degree angle between the hole center connecting line and the stress direction;
fig. 8 is a schematic diagram of a displacement load curve of an experimental sample with a hole center connecting line and a stress direction angle of 90 degrees.
Detailed Description
As shown in fig. 1, in the method for optimizing the strength of the stacked plate cluster hole connection structure according to the present embodiment, the connection dimension, the layering dimension, the number dimension and the space shape dimension of the carbon fiber composite material/titanium alloy connection structure are analyzed by a finite element simulation method, so as to implement an optimal design scheme.
The connection dimension includes: a bolt/nut connection mode and a rivet connection mode on the basis of single-hole connection of the composite material and the titanium alloy, wherein: the rivet connection mode considers the extrusion force of the rivet, and the bolt/nut connection mode considers the pretightening force and the interference quantity.
The layering dimensions include: a single-layer paving mode and a multi-layer paving mode on the basis of single-hole connection, wherein: and analyzing the influence of different layering numbers and sequences on the connection structure.
The number dimension includes: single hole, 2 holes, 3 holes, 4 holes, wherein: the change of the angles of the number of different holes is analyzed, and the optimal parameters of different connection modes and layering modes are determined on the basis of single-hole connection.
The spatial shape dimensions include: triangle, square, diamond/circle, wherein: on the basis of original single-hole connection, the influence of the number of the connecting holes and the formation patterns on the connecting structure is analyzed under the conditions of 2 connecting holes, 3 connecting holes and 4 connecting holes.
The embodiment specifically comprises the following steps:
step one: and establishing a three-dimensional finite element model based on ABAQUS simulation software. On the premise of comprehensively considering material properties, composite material layering sequence, grid density and the like, 10 multiplied by 0.6D cm is established 3 Is a three-dimensional square finite element model of (c).
As shown in Table 1, the material properties are T700/AG80 composite materials, wherein: t700 is a carbon fiber reinforced phase, AG80 epoxy resin is used as a matrix, and the metal and fastener material connected with the composite material is TC4 titanium alloy.
TABLE 1 basic physical Property parameter Table of T700/AG80 composite Material
| Project | Numerical value | Project | Numerical value |
| Tensile strength at 0 degree (MPa) | 2900 | Tensile strength at 90 ° (MPa) | 70 |
| Tensile modulus at 0 degree (GPa) | 140 | Tensile modulus at 90 degrees (GPa) | 8.5 |
| Main Poisson's ratio | 0.28 | Sub poisson ratio | 0.05 |
| 0 degree compressive Strength (MPa) | 0.83 | Compression modulus of 0 degree (GPa) | 222 |
| 90 degree compressive Strength (MPa) | 193 | 90 degree compression modulus (GPa) | 10.2 |
| Flexural Strength at 0 degree (GPa) | 1.23 | Flexural modulus at 0 degree (GPa) | 178 |
| 90 degree flexural Strength (MPa) | 71.6 | 90 degree flexural modulus (GPa) | 7.53 |
| Shear Strength at 0 degree (MPa) | 80.8 |
Damage can cause degradation of composite properties such as elastic modulus and poisson's ratio, and three-dimensional continuous damage mechanical model (CDM) was used to study the damage evolution process. Introducing a damage variable d in a material stiffness matrix i Fiber, matrix, and delamination damage are expressed as:
wherein: based on a two-dimensional in-plane damage variable formula of fiber and matrix damage, considering layered damage conditions of an interlayer out-of-plane direction and a shearing direction, a three-dimensional damage variable calculation mode based on shearing nonlinearity is provided as follows: />
Wherein: d, d it A tensile damage variable, d, representing a fiber or matrix or delamination iC A compressive damage variable representing a fiber or matrix or delamination, d 12 、d 13 、d 23 Representing the lesion variable in three directions.
Based on the assumption of strain equivalence, the three-dimensional orthotropic damage constitutive model of the single-layer plate under the main shaft system of the composite material can be obtained, namely, the relation between the stress tensor and the strain tensor is as follows:
wherein: />
Δ＝1/(1-ν 12 ν 21 (1-d 1 )(1-d 2 )-ν 31 ν 13 (1-d 1 )(1-d 3 )-ν 23 ν 32 (1-d 2 )(1-d 3 )-2ν 21 ν 13 ν 32 (1-d 1 )(1-d 2 )(1-d 3 ))。
And (3) referring to a two-dimensional Hashin criterion and a Ye layering criterion, judging whether the carbon fiber composite material is damaged or failed by adopting an improved three-dimensional Hashin criterion, and judging whether the unit and the structural member are partially damaged or completely failed according to the failure criterion so as to enable the simulation result to be closer to the real condition. The failure mode in the T800 laminated plate layer is judged through stress analysis, a specific simulation flow is shown in fig. 2, and the steps and specific operations comprise:
1) And establishing a three-dimensional composite material/titanium alloy connection structure model in finite element software, sequentially endowing material properties, adopting grid division, setting contact types and load conditions, and submitting files for stress calculation.
2) And as the displacement load increases, the tension force of the structural member gradually increases, and the software calculates the stress of each unit of the structural member and judges whether the unit is damaged according to the material damage failure criterion.
3) If the unit is damaged, setting attenuation on the rigidity of the unit, wherein the method for realizing the rigidity attenuation comprises parameter attenuation, linear attenuation and exponential attenuation; if no damage to the unit occurs, the external force increasing and stress analyzing steps are returned and repeated.
4) When the unit quantity with the rigidity attenuation reaches a preset value, judging that the whole structural member reaches the strength limit, considering the structural member to be broken, and ending the calculation; if the accumulated number of units with the rigidity attenuation does not reach the preset value, the structural member is considered to be degraded, and the external force increasing and stress analyzing steps are repeated.
The failure criterion judging unit refers to: in finite element software, a composite plate model is divided by grids, and cells are obtained through stress analysis.
The failure modes include: fiber tensile failure (sigma) x ≥0)：
Fiber compression failure (sigma) x ＜0)：/>
Matrix tensile failure (sigma) y ≥0)：/>
Matrix compression failure (sigma) y ＜0)：/>
Fiber-matrix shear (sigma) 11 ＞0)：/>
Tensile delamination failure (sigma) 33 ≥0)：/>
Compressive delamination failure (sigma) 33 ＜0)：/>
Wherein: sigma (sigma) 11 、σ 22 Sum sigma 33 Respectively represent the stress of each main direction of the material, tau 12 、τ 23 And τ 13 Respectively indicated shear stress, X in the corresponding direction T And X C Respectively tensile strength and compressive strength along the fiber direction. Y is Y T And Y C The tensile strength and compressive strength of the matrix are shown, respectively. Z is Z T And Z C Respectively, tensile strength and compressive strength perpendicular to the laminate. S is S 12 、S 23 And S is 13 Respectively, the shear strength in the respective directions.
On the basis of an improved three-dimensional Hashin criterion, an energy method is adopted to simulate the damage evolution process of the carbon fiber composite material, and specific damage evolution parameters are as follows:
TABLE 2 carbon fiber composite damage evolution parameters
And 4-dimensional analysis and analysis are carried out on the connection mode, the layering mode, the number of holes and the space shape of the carbon fiber composite material/titanium alloy connection structure so as to realize the optimal design scheme.
Step two: on a single-hole basis, the connection mode of the composite material/titanium alloy is determined.
In the process of bolting, the pretightening force relieves the stress concentration around the plate holes, and reduces layering and fiber breakage; the riveting is suitable for connection between a complex structural member and different materials, has short maintenance time and high cost efficiency, and simultaneously has higher connection reliability. Specific parameters of the contact interference amount and the surface roughness are shown in table 3:
TABLE 3 connection dimension 1 design parameters
| Contact interference quantity (mm) | 0 | 1.5 |
3％D | 4.5％D |
| Surface roughness (mu m) | Smooth surface | Ra3.2 | Ra6.3 | Ra12.5 |
Step three: and on the basis of single holes, analyzing different layering conditions of single-layering and multi-layering carbon fiber composite materials and the like.
The single layer is 0 degree layer, the multiple layers are [ ±90 degrees, 0 degree, ±45 degrees ]10 layers and [ ±90 degrees, ±45 degrees, 0 degree ]10 layers, and the specific parameters are shown in table 4:
TABLE 4 Layered dimension 2 design parameters
| Layering |
0 degree ply | [90°，0°，±45°]Layering | [90°，±45°，0°]Layering |
As shown in fig. 3 to 5, the experimental sample and the stress state diagrams are respectively obtained when the angles of the hole center connecting line and the stress direction are 0 degree, 45 degrees and 90 degrees
Step four: on the basis of original single-hole connection, the influence of the number of the connecting holes and the formation patterns on the connecting structure is analyzed under the conditions of 2 connecting holes, 3 connecting holes and 4 connecting holes.
a) Under the condition of 2 holes, the 2 holes are certain to be collinear, and under the condition that the angle is different from the stress direction in the straight line, the influence of the angle on the connecting structure is analyzed, and specific parameters are shown in table 5:
TABLE 5 design parameters for number dimension 3 in two hole case
| Angle of | 0° | 45° | 90° |
b) Under the condition of 3 holes, the 3 holes are collinear or form a triangle, and the change of the angle is analyzed in the collinear way; analyzing the influence of the side length on the connection structure under the condition of different side lengths of the triangle when the triangle is formed; in the graph dimension, the effect of 6-hole and 9-hole triangles on the connection structure is analyzed on the assumption that the side length is unchanged and is fixed to be 60mm. The specific parameters are shown in Table 6:
table 6 design parameters for number dimension 3 and graphic dimension 4 in the three hole case
| Angle of | 0° | 45° | 90° |
| Triangle side length (mm) | 40 | 50 | 60 |
| Number of |
3 | 6 | 9 |
c) Under the condition of 4 holes, 4 holes are collinear or form a square or form a diamond/round shape, and the change of angles is analyzed when the 4 holes are collinear; analyzing the influence of the side length on the connection structure under the condition of different side lengths of the square when the square is formed; analysis of the effect of radius on the connection structure in the case of different radii of the diamond/circle when the diamond/circle was composed. In the dimension of the graph, assuming that the side length is unchanged and is fixed to be 60mm, analyzing the influence of 8-hole squares and 12-hole squares on the connecting structure; the effect of the circles of 5 and 6 holes on the connection structure was analyzed assuming a constant radius, fixed at 35 mm. The specific parameters are shown in Table 7:
TABLE 7 design parameters for number dimension 3 and graphic dimension 4 for the four hole case
Step five: the shear and tensile loads are input as boundary conditions, and the shear and tensile strength of the composite material/titanium alloy connection structure are output as results.
In the embodiment, an M6 bolt connection mode is adopted, and under the condition of double-hole single lap joint of the composite material laminated plate and the titanium alloy plate, the angle influence of hole center connecting lines and the stress direction is studied. The contact interference amount is 0, the contact surface is smooth, and the layering mode is [90 degrees (+/-45 degrees) and 0 degrees] 5s . A tensile displacement load is applied. According to simulation calculation, the limit load of the experimental sample piece with the hole center connecting line and the stress direction angle being 0 degree is 4933kN, the corresponding tensile displacement is 0.18mm, the limit load of the experimental sample piece with the hole center connecting line and the stress direction angle being 45 degrees is 2161kN, the corresponding tensile displacement is 0.07mm, the limit load of the experimental sample piece with the hole center connecting line and the stress direction angle being 90 degrees is 4067kN, and the corresponding tensile displacement is 0.27mm. According to the improved three-dimensional Hashin damage failure criterion, the carbon fiber composite laminated plate has the earliest matrix failure and interlayer delamination and finally has fiber failure.
Compared with the prior art, the method can systematically design the strength of the cluster hole connection structure from 4 dimensions of a connection mode, a layering mode, the number of holes and a space shape, so as to realize the maximization of the tensile strength.
The foregoing embodiments may be partially modified in numerous ways by those skilled in the art without departing from the principles and spirit of the invention, the scope of which is defined in the claims and not by the foregoing embodiments, and all such implementations are within the scope of the invention.
Claims (1)
1. A stacked sheet material cluster hole test system, comprising: a composite plate/titanium alloy connection module, a fastener, and a clamp for connecting the test sample with the tensile testing machine;
drilling at the upper and lower boundaries of the composite material plate in the composite material plate/titanium alloy connecting module
Uniformly arranged small holes;
the position, which is contacted with the clamp, of the composite material plate in the composite material plate/titanium alloy connecting module is reinforced by a metal sheet, the metal sheet is reinforced by an aluminum alloy material, and the aluminum alloy reinforcing sheet is bonded with the composite material plate by an acrylic structural adhesive;
the aluminum alloy reinforcing sheet is provided with
The positions of the holes and the centers of the holes coincide with the positions of the holes at the edge of the composite material plate, and the hole diameter is smaller than that of the holes on the composite material plate so as to avoid the composite material plate from being broken at the edge at first;
the laminated plate cluster hole test is as follows:
step one: designing a constitutive model of the composite material and a material failure criterion by using finite element simulation software, and establishing a three-dimensional composite material/titanium alloy laminated plate model;
step two: on the basis of a single-hole laminated plate, different connecting modes of composite materials/titanium alloys are replaced, namely different fastener types are adopted to obtain the influence evaluation of the different fastener types on the laminated plate structure;
step three: on the basis of a single-hole laminated plate, two different layering modes of single-layering and multi-layering carbon fiber composite materials are adopted to obtain the influence evaluation of different layering angles of the composite materials on the laminated plate structure;
step four: on the basis of the original single-hole connection of the laminated plate, the number of the connecting holes is changed to obtain the number of the connecting holes, and the influence evaluation of the formed graph on the bearing performance of the connecting structure is performed;
step five: according to the actual connection mode and stress condition of the three-dimensional composite material/titanium alloy laminated plate model, the three-dimensional composite material/titanium alloy laminated plate model is sequentially subjected to finite element simulation software: setting material properties, selecting grid cell types, performing grid division, setting contact properties, inputting tensile load boundary conditions, and obtaining a tensile strength simulation result of the composite material/titanium alloy connection structure;
ABAQUS or ANSYS adopted by the finite element simulation constructs a composite material solid model in a composite material module embedded in software, and is connected with a titanium alloy plate through a fastenerMatched together to build a three-dimensional composite material/titanium alloy laminated plate model, which is specifically as follows: introducing a damage variable d in a material stiffness matrix i Fiber, matrix, and delamination damage are expressed as:
wherein: based on a two-dimensional in-plane damage variable formula of fiber and matrix damage, considering layered damage conditions of an interlayer out-of-plane direction and a shearing direction, a three-dimensional damage variable calculation mode based on shearing nonlinearity is provided as follows: />
Wherein: d, d it A tensile damage variable, d, representing a fiber or matrix or delamination iC A compressive damage variable representing a fiber or matrix or delamination, d 12 、d 13 、d 23 A lesion variable representing three directions;
the constitutive model is used for constructing a nonlinear constitutive relation of the composite material in material properties according to the anisotropic characteristic of the composite material, and specifically comprises the following steps: the relationship between stress tensors and strain tensors is:
Δ＝1/(1-ν 12 ν 21 (1-d 1 )(1-d 2 )-ν 31 ν 13 (1-d 1 )(1-d 3 )-ν 23 ν 32 (1-d 2 )(1-d 3 )-2ν 21 ν 13 ν 32 (1-d 1 )(1-d 2 )(1-d 3 ))；
the material failure criterion is that a three-dimensional Hashin criterion is set in finite element simulation to serve as a composite material failure criterion, and a failure mode is judged through stress analysis;
the failure modes include: fiber tensile failure (sigma) x ≥0)：
Fiber compression failure (sigma) x ＜0)：/>
Matrix tensile failure (sigma) y ≥0)：/>
Matrix compression failure (sigma) y ＜0)：/>
Fiber-matrix shear (sigma) 11 ＞0)：/>
Tensile delamination failure (sigma) 33 ≥0)：/>
Compressive delamination failure (sigma) 33 ＜0)：/>
Wherein: sigma (sigma) 11 、σ 22 Sum sigma 33 Respectively represent the stress of each main direction of the material, tau 12 、τ 23 And τ 13 Respectively indicated shear stress, X in the corresponding direction T And X C Respectively representing tensile strength and compressive strength along the fiber direction, Y T And Y C Respectively representing the tensile strength and the compressive strength of the matrix, Z T And Z C Respectively represent tensile strength and compressive strength perpendicular to the laminate, S 12 、S 23 And S is 13 Respectively representing the shear strength in the respective directions;
the fastener type comprises bolting and riveting, and when the bolting mode is adopted, the interference quantity range is set to be 0-4.5% so as to obtain the optimal matching quantity to realize the maximum strength of the connecting structure;
the single-layer refers to: the layering of the composite material is in a single direction and is 0 DEG, 45 DEG, -45 DEG or 90 DEG; the multi-layering means: the layering of the composite material is in multiple directions and is [90 °,0 °, ±45° ], [90 °,0 °, ±45° ];
the changing the number of the connecting holes comprises the following steps: 2, 3 or 4 connection holes, wherein:
the 2 connecting holes refer to: 2 holes are in certain collineation, and the influence of the angle on the connecting structure is analyzed under the condition that the angle is different from the stress direction;
the 3 connecting holes refer to: the 3 holes are collinear or form a triangle, and the change of the angle is analyzed in the collinear way; analyzing the influence of the side length on the connection structure under the condition of different side lengths of the triangle when the triangle is formed;
the 4 connecting holes refer to: 4 holes are collinear or form square or form diamond/round, and the change of angles is analyzed when the holes are collinear; when the square is formed, analyzing the influence of the side length on the connection structure under the condition of different side lengths of the square; analyzing the influence of the radius on the connection structure under the condition of different radii of the diamond/round shape when the diamond/round shape is formed;
in the dimension of the graph, when the side length of the square is fixed or the radius of the circle is fixed, the influence of the number of the holes on the connecting structure is analyzed.
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