CN112100744A - Strength optimization method of laminated plate cluster hole connecting structure - Google Patents

Strength optimization method of laminated plate cluster hole connecting structure Download PDF

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CN112100744A
CN112100744A CN202010913757.5A CN202010913757A CN112100744A CN 112100744 A CN112100744 A CN 112100744A CN 202010913757 A CN202010913757 A CN 202010913757A CN 112100744 A CN112100744 A CN 112100744A
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composite material
holes
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安庆龙
刘畅
陈明
王贤锋
明伟伟
于思泓
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Shanghai Jiaotong University
Shanghai Aircraft Manufacturing Co Ltd
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Abstract

A strength optimization method for a cluster hole connecting structure of laminated plates is characterized in that 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 holes of a composite laminated plate are explored from a microscopic angle, and the optimal design of the strength of the cluster hole composite/titanium alloy laminated plate connecting structure is realized from a structural angle by simulating and analyzing the influence rule of the number and spatial layout of holes on the static strength of the connecting structure. The invention realizes the optimized design of the strength of the cluster hole of the composite material/titanium alloy laminated plate connecting structure from the structural design angle.

Description

Strength optimization method of laminated plate cluster hole connecting structure
Technical Field
The invention relates to a technology in the field of composite material structures, in particular to a strength optimization method for a laminated plate cluster hole connecting structure for improving the bearing performance of a carbon fiber composite material and titanium alloy connecting 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 concerned and applied in the design and manufacture of large airliners and spacecrafts. The carbon fiber composite material is mainly applied to wings, empennages and airframes of airplanes and more main load-bearing structural members, so that the reinforcing of the connection performance of the carbon fiber composite material is very important. At present, the connection methods of the carbon fiber composite material laminated plates are mainly 5, namely mechanical connection, adhesive connection, sewing connection, Z-pin connection and mechanical connection/adhesive connection hybrid connection. Due to the fact that the carbon fiber composite material is low in shearing strength and tensile strength and poor in shaping, stress concentration occurs around the hole after drilling, and therefore the connecting structure is prone to damage.
A unified evaluation system is not yet determined in the field of the existing composite material connecting structure, and the problems of low assembling efficiency, poor seaworthiness evaluation effect and the like of the composite material connecting structure exist, so that the feasibility of wide application of the composite material is influenced. In the field of composite material plate cluster hole design, how to improve the strength of the composite material plate and the bearing performance of a composite material laminated plate connecting structure in a limited plate size range by reasonably designing the laying mode of the composite material plate, the connecting mode of the laminated plate and the spatial distribution and size of the cluster holes, a complete cluster hole evaluation system is formed, and the method is a domestic blank and needs to be researched urgently.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a strength optimization method of a laminated plate clustered hole connecting structure, which researches the progressive damage expansion and failure modes of fibers and matrixes around a laminated plate hole of a composite material from a microscopic angle by establishing a progressive damage model and adopting Hashin failure criterion, and realizes the optimized design of the strength of the clustered hole of the laminated plate connecting structure of the composite material/titanium alloy from the structural design angle by simulating and analyzing the influence rule of the number and the spatial layout of the holes on the static strength of the connecting structure.
The invention is realized by the following technical scheme:
the invention relates to a strength optimization method of a laminated plate cluster hole connecting structure, which comprises the following steps of:
the method comprises the following steps: and (3) 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.
The finite element simulation adopts, but is not limited to ABAQUS or ANSYS, a composite material solid model is constructed in a composite material module embedded in software, and the composite material solid model and the titanium alloy sheet material are connected and assembled together through a fastener, so that a three-dimensional composite material/titanium alloy laminated plate model is established.
The constitutive model is used for constructing the nonlinear constitutive relation of the composite material in the material property aiming at the anisotropic characteristic of the composite material.
The material failure criterion is characterized in that a three-dimensional Hashin criterion is set in finite element simulation to serve as a composite material failure criterion.
Step two: on the basis of the single-hole laminated plate, different composite material/titanium alloy connection modes are replaced, namely different fastener types are adopted to obtain the evaluation of the influence of the different fastener types on the laminated plate structure.
The type of the fastener includes bolt connection and rivet connection, and when the bolt connection is adopted, the interference amount is set to be in the range of 0-4.5% to obtain the optimum fit amount to achieve the maximum strength of the connection structure.
The fastener material adopts titanium alloy material widely applied to aviation airplanes.
Step three: on the basis of the single-hole laminated plate, the influence evaluation of different laminating angles of the composite material on the laminated plate structure is obtained by adopting two different laminating modes of a single-layer laminating mode and a multi-layer laminating mode.
The single paved layer is as follows: the plies of the composite material are unidirectional, preferably 0/45/90.
The multi-layer refers to that: the plies of the composite material are in multiple directions, preferably [90 °, 0 °, ± 45 ° ], and the like.
Step four: on the basis of the original laminated plate single-hole connection, the number of the connecting holes is changed to obtain the number of the connecting holes and the influence evaluation of the formed patterns on the bearing performance of the connecting structure.
The change of the number of the connecting holes comprises the following steps: 2 connecting holes, 3 connecting holes or 4 connecting holes, wherein:
the 2 connecting holes refer to: the 2 holes must be collinear, and the effect of the angle on the connection, for example 0 °/45 °/90 °, is evaluated in the case of different angles of variation of this line from the direction of the force.
The 3 connecting holes refer to: 3 holes are collinear or form a triangle, and the change of the angle is analyzed when the holes are collinear, such as 0 degrees/45 degrees/90 degrees; the composition of the triangle is evaluated by the effect of the side length on the connection, for example 40mm/50mm/60mm, in the case of a triangle of different side lengths. In the graphical dimension, the influence of the number of holes on the connection structure, e.g. 3 holes/6 holes/9 holes, is analyzed assuming that the side length of the triangle is constant.
The 4 connecting holes refer to: the 4 holes are collinear or form squares or form rhomb/circles, and the change in angle is analyzed when collinear, for example, 0 °/45 °/90 °.
When composing a square, the effect of the side length on the connection structure is analyzed in the case of squares of different side lengths, for example 40mm/50mm/60 mm. The rhombus/circle is formed by analyzing the influence of the radius on the connecting structure in the case of different radii of the rhombus/circle, such as R15/R25/R35. In the dimension of the graph, when the side length of the square is constant, the influence of the number of holes on the connection structure is analyzed, for example, 4 holes/8 holes/12 holes. The effect of the number of holes on the connection structure, e.g. 4 holes/5 holes/6 holes, is analyzed assuming a constant radius of the circle.
Step five: according to the actual connection mode and the stress condition of the three-dimensional composite material/titanium alloy laminated plate model, sequentially: setting material properties, selecting the type of a grid unit, carrying out grid division, setting contact properties, and inputting tensile load boundary conditions to obtain a tensile strength simulation result of the composite material/titanium alloy connecting structure.
The invention relates to a test system for realizing the method, which comprises the following steps: the device comprises a composite plate/titanium alloy connecting module, a fastener and a clamp for connecting a test sample piece with a tensile testing machine.
In order to ensure that the test sample piece is subjected to uniform tensile load, the upper boundary and the lower boundary of the composite material plate in the composite material plate/titanium alloy connecting module are drilled
Figure BDA0002664306540000031
The small holes are uniformly distributed.
The composite material plate/titanium alloy connecting module is characterized in that the position, in contact with the clamp, of the composite material plate is reinforced by a metal sheet, the metal sheet is preferably reinforced by 7075 aluminum alloy materials, and the aluminum alloy reinforcing sheet and the composite material plate are bonded by Swiss ergo 1690 acrylic acid structural adhesive.
The aluminum alloy reinforcing sheet is provided with
Figure BDA0002664306540000032
The hole center position of the small hole is superposed with the position of the small hole at the edge of the composite material plate, and the aperture of the small hole is smaller than that of the small hole on the composite material plate, so that the composite material plate is prevented from being broken at the edge at first.
Technical effects
The invention integrally solves the problems that a unified evaluation system is not yet determined in the field of the existing composite material connecting structure, and the composite material connecting structure has low assembly efficiency and poor seaworthiness evaluation effect. Through the strength maximization scheme of the cluster hole composite material/titanium alloy connecting structure, the tensile strength of the connecting structure is maximized from four dimensions of a connecting mode, a layering mode, the number of holes and a space shape.
The method provided by the invention is characterized in that a progressive damage model is established, an improved three-dimensional Hashin failure criterion is adopted, progressive damage expansion and failure modes of fibers and a matrix around the holes of the composite laminated plate are explored from a microscopic angle, and the influence rule of the number and the spatial layout of the holes on the static strength of the connecting structure is analyzed through simulation, so that the optimal design of the strength of the connecting structure of the composite/titanium alloy laminated plate with the cluster holes is realized from a structural angle.
Drawings
FIG. 1 is a schematic flow diagram of the process of the present invention;
FIG. 2 is a flow diagram of an embodiment simulation analysis;
FIG. 3 is a schematic view of an experimental sample piece and a stress state when an angle between a hole center connecting line and a stress direction is 0 degree;
FIG. 4 is a schematic view of an experimental sample piece and a stress state when an angle between a hole center connecting line and a stress direction is 45 degrees;
FIG. 5 is a schematic view of an experimental sample piece and a stress state when an angle between a hole center connecting line and a stress direction is 90 degrees;
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 schematic view of a displacement load curve of an experimental sample piece with a hole center connecting line and a stress direction angle of 0 degree;
FIG. 7 is a schematic view of a displacement load curve of an experimental sample piece with a hole center connecting line and a stress direction angle of 45 degrees;
FIG. 8 is a schematic view of a displacement load curve of an experimental sample piece with a hole center connecting line and a stress direction angle of 90 degrees.
Detailed Description
As shown in fig. 1, for the method for optimizing strength of a laminated plate cluster hole connection structure according to this embodiment, analysis and analysis of connection dimension, stacking dimension, number dimension, and spatial shape dimension are performed on a carbon fiber composite/titanium alloy connection structure by a finite element simulation method, so as to implement an optimal design solution.
The connection dimension comprises: bolt/nut connection mode, rivet connection mode on combined material and titanium alloy haplopore connection basis, wherein: the extrusion force of the rivet is considered in the rivet connection mode, and the pretightening force and the interference quantity are considered in the bolt/nut connection mode.
The ply dimensions include: a single-layer laying mode and a multi-layer laying mode on the basis of single-hole connection, wherein: and analyzing the influence of different layering quantities and sequences on the connecting structure.
The number dimension includes: single well, 2 wells, 3 wells, 4 wells, wherein: the variation of the number and the angle of different holes is analyzed, and the embodiment determines the optimal parameters in different connection modes and layering modes on the basis of single-hole connection.
The spatial shape dimension comprises: triangle, square, rhomb/circle, wherein: on the basis of the original single-hole connection, the influence of the number of the connecting holes and the formed patterns on the connecting structure under the conditions of 2 connecting holes, 3 connecting holes and 4 connecting holes is analyzed.
The embodiment specifically comprises the following steps:
the method comprises the following steps: 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 established3The three-dimensional square finite element model of (1).
As shown in Table 1, the material property is T700/AG80 composite material, wherein: t700 is carbon fiber reinforced phase, AG80 epoxy resin is matrix, and metal and fastener material connected with the composite material is TC4 titanium alloy.
TABLE 1 basic physical Properties of the T700/AG80 composite Material
Item Numerical value Item Numerical value
0 degree tensile Strength (MPa) 2900 Tensile strength at 90 ° (MPa) 70
0 degree tensile modulus (GPa) 140 Tensile modulus at 90 ° (GPa) 8.5
Principal poisson's ratio 0.28 Sub-poisson's ratio 0.05
0 degree compressive Strength (MPa) 0.83 0 degree compressive modulus (GPa) 222
90 degree compressive Strength (MPa) 193 90 degree compressive modulus (GPa) 10.2
0 degree bending strength (GPa) 1.23 0 degree flexural modulus (GPa) 178
90 degree bending Strength (MPa) 71.6 90 DEG flexural modulus (GPa) 7.53
0 degree shear strength (MPa) 80.8
The damage can cause the degradation of the properties (such as elastic modulus and Poisson ratio) of the composite material, and a three-dimensional continuous damage mechanical model (CDM) is adopted to research the damage evolution process of the composite material. Introduction of a damage variable d into a material stiffness matrixiThen the fiber, matrix and delamination damage is expressed as:
Figure BDA0002664306540000041
wherein: based on a two-dimensional in-plane damage variable formula of fiber and matrix damage, the layered damage conditions of the outer direction of an interlayer plane and the shearing direction are considered, and a three-dimensional damage variable calculation mode based on shearing nonlinearity is provided as follows:
Figure BDA0002664306540000051
wherein: ditRepresenting the tensile damage variable of the fibre or matrix or of the layer, diCRepresenting the compression damage variable of the fibre or matrix or of the layer, d12、d13、d23Representing damage variables in three directions.
Based on the assumption of strain equivalence, a three-dimensional orthotropic damage constitutive model of the single-layer plate under the composite material principal axis system can be obtained, namely the relationship between the stress tensor and the strain tensor is as follows:
Figure BDA0002664306540000052
wherein:
Figure BDA0002664306540000053
Figure BDA0002664306540000054
Figure BDA0002664306540000055
Figure BDA0002664306540000056
Figure BDA0002664306540000057
Δ＝1/(1-ν12ν21(1-d1)(1-d2)-ν31ν13(1-d1)(1-d3)-ν23ν32(1-d2)(1-d3)-2ν21ν13ν32(1-d1)(1-d2)(1-d3))。
and with reference to a two-dimensional Hashin criterion and a Ye layering criterion, the carbon fiber composite material adopts the improved three-dimensional Hashin criterion to judge whether the unit and the structural member are partially damaged or completely failed according to the failure criterion, so that the simulation result is closer to the real condition. The failure mode in the T800 laminated plate layer is judged through stress analysis, and the specific simulation flow is shown in FIG. 2, and the steps and the specific operation thereof comprise:
1) establishing a three-dimensional composite material/titanium alloy connection structure model in finite element software, sequentially giving material attributes, adopting grid division, setting contact types and load conditions, and submitting a file for stress calculation.
2) Along with the increase of the displacement load, the tensile force borne by the structural part is gradually increased, the software calculates the stress of each unit of the structural part, and whether the unit is damaged or not is judged according to the material damage failure criterion.
3) If the unit is damaged, attenuation is set for the rigidity of the unit, and the method for realizing rigidity attenuation comprises parameter attenuation, linear attenuation and exponential attenuation; if the unit is not damaged, the external force addition and stress analysis steps are returned and repeated.
4) When the number of units with rigidity attenuation reaches a preset value, judging that the whole structural part reaches the strength limit, considering that the structural part is broken, and then finishing the calculation; and if the accumulated number of the units with the rigidity attenuation does not reach the preset value, the structural part is considered to have material degradation, and the steps of external force increase and stress analysis are repeated.
The failure criterion judging unit is as follows: in the finite element software, the composite plate model is divided by grids, and units are obtained through stress analysis.
The failure modes include: fiber tensile failure (σ)x≥0)：
Figure BDA0002664306540000061
Fibre compression failure (sigma)x＜0)：
Figure BDA0002664306540000062
Elongation failure (σ) of matrixy≥0)：
Figure BDA0002664306540000063
Compression failure (σ) of matrixy＜0)：
Figure BDA0002664306540000064
Fiber-matrix shear (σ)11＞0)：
Figure BDA0002664306540000065
Tensile delamination failure (σ)33≥0)：
Figure BDA0002664306540000066
Compressive layered failure (σ)33＜0)：
Figure BDA0002664306540000067
Wherein: sigma11、σ22And σ33Respectively representing the stress in each principal direction of the material, tau12、τ23And τ13Respectively indicated shear stress in the respective directions, XTAnd XCRespectively along the fiberTensile strength and compressive strength. Y isTAnd YCRespectively, the tensile strength and the compressive strength of the matrix. ZTAnd ZCTensile strength and compressive strength perpendicular to the laminate are indicated, respectively. S12、S23And S13Respectively, 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 Damage evolution parameters of carbon fiber composites
Figure BDA0002664306540000068
And 4-dimensional analysis and analysis are carried out on the carbon fiber composite material/titanium alloy connecting structure in a connecting mode, a layering mode, the number of holes and the space shape so as to realize an optimal design scheme.
Step two: on the basis of a single hole, the connection mode of the composite material/titanium alloy is determined.
In the process of bolt connection, the pretightening force relieves the stress concentration around the plate hole, and the layering and fiber breakage are reduced; the riveting is suitable for connection between a complex structural member and different materials, the maintenance time is short, the cost benefit is high, and meanwhile, the riveting device also has high connection reliability. Specific parameters of the amount of contact interference and the surface roughness are shown in table 3:
table 3 connecting dimension 1 design parameters
Contact interference quantity (mm) 0 1.5％D 3％D 4.5％D
Surface roughness (μm) Smooth surface Ra3.2 Ra6.3 Ra12.5
Step three: on the basis of a single hole, different layering conditions of a single-layered carbon fiber composite material, a multi-layered carbon fiber composite material and the like are analyzed.
The single ply is a 0-degree ply, the multi-ply is a 10-ply with +/-90 degrees, 0 degrees, +/-45 degrees and +/-10-ply with +/-90 degrees, +/-45 degrees and 0 degrees, and the specific parameters are shown in the table 4:
TABLE 4 lay-up dimension 2 design parameters
Layering mode 0 degree ply [90°，0°，±45°]Ply [90°，±45°，0°]Ply
As shown in fig. 3 to 5, specifically, the differences between the three methods are as follows: ......
Step four: on the basis of the original single-hole connection, the influence of the number of the connecting holes and the formed patterns on the connecting structure under the conditions of 2 connecting holes, 3 connecting holes and 4 connecting holes is analyzed.
a) Under the 2 hole circumstances, 2 holes must be collineation, and the analysis is under the different angle of change conditions of this straight line and atress direction, and the angle is to connection structure's influence, and specific parameter is as shown in Table 5:
TABLE 5 design parameters for the two-hole case, number dimension 3
Angle of rotation 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 when the 3 holes are collinear; when the triangle is formed, the influence of the side length on the connecting structure under the condition of different side lengths of the triangle is analyzed; in the dimension of the graph, the influence of the triangle with 6 holes and 9 holes on the connecting structure is analyzed on the assumption that the side length is constant and is fixed to be 60 mm. The specific parameters are shown in table 6:
TABLE 6 design parameters for the three-hole case, number dimension 3 and graphics dimension 4
Angle of rotation 0° 45° 90°
Triangle side length (mm) 40 50 60
Number of triangular holes 3 6 9
c) Under the condition of 4 holes, the 4 holes are collinear or form a square or a rhombus/circle, and the change of angles is analyzed when the 4 holes are collinear; when the square is formed, the influence of the side length on the connecting structure under the condition that the square is different in side length is analyzed; the influence of the radius on the connection structure in the case of different radii of the rhombus/circle is analyzed when the rhombus/circle is composed. In the dimension of the graph, assuming that the side length is constant and is fixed to be 60mm, analyzing the influence of squares with 8 holes and 12 holes on a connecting structure; the effect of the circularity 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 the number dimension 3 and the graphic dimension 4 for the four-hole case
Figure BDA0002664306540000071
Figure BDA0002664306540000081
Step five: and inputting shearing and tensile loads as boundary conditions, and outputting the shearing and tensile strength of the composite material/titanium alloy connecting structure as a result.
In the embodiment, the M6 bolt connection mode is adopted, and the composite laminated plate and the titanium are combinedUnder the condition of double-hole single-lap joint of the alloy plate, the influence of the angle between the hole center connecting line and the stress direction is researched. The contact interference amount is 0, the contact surface is smooth, and the layering mode is [90 °, +/-45 °, 0 ° ]]5s. A tensile displacement load is applied. Through simulation calculation, the limit load of the experimental sample piece with the hole center connecting line and the stress direction angle of 0 degrees 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 of 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 of 90 degrees is 4067kN, and the corresponding tensile displacement is 0.27 mm. According to the improved three-dimensional Hashin damage failure criterion, the carbon fiber composite laminated board firstly generates matrix failure and interlayer delamination, and finally generates fiber failure.
Compared with the prior art, the method can perform systematic strength design from 4 dimensions of a connection mode, a layering mode, the number of holes and a space shape aiming at the cluster hole connection structure so as to realize the maximization of tensile strength.
The foregoing embodiments may be modified in many different ways by those skilled in the art without departing from the spirit and scope of the invention, which is defined by the appended claims and all changes that come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.

Claims (9)

1. A method for realizing cluster holes of laminated plates is characterized by comprising the following specific steps:
the method comprises the following steps: designing a constitutive model of the composite material and a material failure criterion and establishing a three-dimensional composite material/titanium alloy laminated plate model by using finite element simulation software;
step two: on the basis of the single-hole laminated plate, different connecting modes of composite materials/titanium alloys are replaced, namely different fastener types are adopted to obtain the evaluation of the influence of the different fastener types on the laminated plate structure;
step three: on the basis of the single-hole laminated plate, the influence evaluation of different laminating angles of the composite material on the laminated plate structure is obtained by adopting two different laminating modes of a single-layer laminating and a multi-layer carbon fiber composite material;
step four: on the basis of the original laminated plate single-hole connection, the number of the connecting holes is changed to obtain the number of the connecting holes and the influence evaluation of the formed pattern on the bearing performance of the connecting structure;
step five: according to the actual connection mode and the stress condition of the three-dimensional composite material/titanium alloy laminated plate model, sequentially: setting material properties, selecting the type of a grid unit, carrying out grid division, setting contact properties, and inputting tensile load boundary conditions to obtain a tensile strength simulation result of the composite material/titanium alloy connecting structure.
2. A method for realizing cluster holes in laminated sheets as claimed in claim 1, wherein the finite element simulation is performed by ABAQUS or ANSYS, and a solid model of composite material is constructed in a composite material module embedded in software, and is connected and assembled with the titanium alloy sheets by fasteners, thereby establishing a three-dimensional composite material/titanium alloy laminated sheet model;
the constitutive model is used for constructing a nonlinear constitutive relation of the composite material in the material property aiming at the anisotropic characteristic of the composite material;
the material failure criterion is characterized in that a three-dimensional Hashin criterion is set in finite element simulation to serve as a composite material failure criterion.
3. The laminated plate cluster hole realization method as claimed in claim 1, wherein the fastener type comprises bolt connection and rivet connection, and when the bolt connection is adopted, the interference amount is set to be in the range of 0-4.5% to obtain the optimum fit amount to realize the maximum strength of the connection structure.
4. The method of claim 1, wherein the single-layer is selected from the group consisting of: the layering of the composite material is in a single direction and is 0 degree, 45 degrees, -45 degrees or 90 degrees; the multi-layer refers to that: the plies of the composite material are multi-directional and are [90 °, 0 °, ± 45 ° ], [90 °, 0 °, ± 45 ° ].
5. The laminated plate cluster hole implementation method as claimed in claim 1, wherein the changing of the number of connection holes comprises: 2 connecting holes, 3 connecting holes or 4 connecting holes, wherein:
the 2 connecting holes refer to: 2, the holes are collinear, and the influence of the angle on the connecting structure under the condition that the angle is changed in different directions of the straight line and the stress direction is analyzed;
the 3 connecting holes refer to: 3, the holes are collinear or form a triangle, and the change of the angle is analyzed when the holes are collinear; when the triangle is formed, the influence of the side length on the connecting structure under the condition of different side lengths of the triangle is analyzed;
the 4 connecting holes refer to: 4 holes are collinear or form a square or a rhombus/circle, 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 connecting structure under the condition that the square has different side lengths; analyzing the influence of the radius on the connecting structure under the condition of different radiuses of the rhombus/circle when the rhombus/circle 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.
6. A test system for carrying out the method of any preceding claim, comprising: the device comprises a composite plate/titanium alloy connecting module, a fastener and a clamp for connecting a test sample piece with a tensile testing machine.
7. The testing system of claim 6, wherein the composite plate/titanium alloy connecting module is drilled at the upper and lower boundaries of the composite plate
Figure FDA0002664306530000021
Uniformly arranged small holes.
8. The test system according to claim 6, wherein the composite material plate/titanium alloy connecting module is reinforced by a metal sheet at the position where the composite material plate is contacted with the clamp, the metal sheet is reinforced by an aluminum alloy material, and the aluminum alloy reinforcing sheet is bonded with the composite material plate by acrylic structural adhesive.
9. The testing system of claim 6, wherein said aluminum alloy reinforcing sheet is provided with a plurality of protrusions
Figure FDA0002664306530000022
The hole center position of the small hole is superposed with the position of the small hole at the edge of the composite material plate, and the aperture of the small hole is smaller than that of the small hole on the composite material plate, so that the composite material plate is prevented from being broken at the edge at first.
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