CN108681650A - A kind of warp-knitted spacer fabric composite material stress analysis method - Google Patents
A kind of warp-knitted spacer fabric composite material stress analysis method Download PDFInfo
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- CN108681650A CN108681650A CN201810530415.8A CN201810530415A CN108681650A CN 108681650 A CN108681650 A CN 108681650A CN 201810530415 A CN201810530415 A CN 201810530415A CN 108681650 A CN108681650 A CN 108681650A
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- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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Abstract
The invention discloses a kind of warp-knitted spacer fabric composite material stress analysis method, this method establishes the structural model of warp-knitted spacer fabric enhancing polyurethane enhancing composite material including the use of finite element software；The parameters of finite element model are set, and the parameter includes paraphysis parameter, warp-knitted spacer fabric enhancing compound polyurethane material structural parameters between the band yarn mode for being spaced sley bar, each point and band yarn number correspondence, space fabric；According to carrying out mesh generation the characteristics of physical model.The stress compression rate curve obtained through finite element analysis by method provided by the present application is compared with compression test curve, although there are a small amount of deviations for the stress compression rate curve and trial curve of COMPOSITE FINITE ELEMENT simulation, but finite element modelling result provided by the present application still can reflect the variation tendency of sample compression performance well, and the theoretical foundation of structure design can be provided for the application in Practical Project.
Description
Technical field
The present invention relates to material property analysis technical fields, more particularly to a kind of warp-knitted spacer fabric composite material stress
Analysis method.
Background technology
Warp-knitted spacer fabric has excellent incompressible, shock resistance and higher production efficiency, uses it as enhancing
The composite material of body has preferable mechanical property in thickness direction, can significantly improve interlaminar shear strength, and by outer
Boundary's load especially Dynamic Loading when, the phenomenon that being not in layering.Good structural intergrity, impact resistance and low
Honest and clean production cost makes warp-knitted spacer fabric enhancing compound polyurethane material be expected to become a kind of New Buffering material.
But in the prior art, the variation for enhancing the compression performance of compound polyurethane material due to lacking warp-knitted spacer fabric
Trend theoretical foundation instructs so that space fabric enhancing compound polyurethane material carries out needs when structure design in process of production
Experiment repeatedly is carried out using authentic material, so that the cost of manufacturer greatly increases.
Invention content
The present invention provides a kind of warp-knitted spacer fabric composite material stress analysis methods.
The present invention provides following schemes：
A kind of warp-knitted spacer fabric composite material stress analysis method, including：
Using finite element software, the structural model of warp-knitted spacer fabric enhancing polyurethane enhancing composite material is established；
The parameters of finite element model are set, and the parameter includes being spaced band yarn mode, each point and the band yarn number of sley bar
Paraphysis parameter, warp-knitted spacer fabric enhance compound polyurethane material structural parameters between code correspondence, space fabric；
According to carrying out mesh generation the characteristics of physical model；
Physical model to having divided grid, which applies load and enters post-processing function, generates the warp-knitted spacer fabric increasing
The load-deformation curve of strong compound polyurethane material.
Preferably：The structural model of warp-knitted spacer fabric enhancing polyurethane enhancing composite material is established, including：
A minimum complete loop structure unit is chosen as represented volume element, the represented volume element is two every comb
Comb a complete band yarn cycle be formed by fabric construction unit and comprising polyurethane foam matrix, the representative to selection
Body unit carries out finite element analysis and establishes structural model.
Preferably：Single paraphysis model is established according to the movement locus every sley bar；Successively to single paraphysis entity mould
Type carries out mirror image, array processing, forms the 3-D geometric model of paraphysis overall alignment between two interval sley bars；
Establish the upper and lower surface of warp-knitted spacer fabric enhancing compound polyurethane material；
It carries out the 3-D geometric model on established upper and lower surface and paraphysis overall alignment to cohere assembly and be spaced
Fabric substantive model；
Establish a polyurethane foam physical model isometric with space fabric；
Space fabric physical model and polyurethane foam physical model are assembled to get to the structural model.
Preferably：The single paraphysis method for establishing model include：Initially set up point coordinates A, B, C, D.Then two
In a x-z-plane, straight line tie point A, B and point C, D are used respectively；And in y-z plane, an intermediate point O is selected, with round and smooth song
Line connects point B, O with C；Using point A as the center of circle, 0.1mm is that radius does a circle in x-y plane, and this disc is prolonged space
Curve ABCD, which is pulled, generates single paraphysis physical model.
Preferably：According to carrying out mesh generation the characteristics of physical model；Including：
Mesh generation is carried out using free mesh in finite element software；Set physical model surface mesh thickness,
Quality, physical grid type parameter carry out mesh generation using grid Core Generator to physical model.
Preferably：Physical model to having divided grid applies load, including：
One end of the physical model is constrained, the other end applies compressive load to realize；In the physical model upper surface side z
Upwards when compression, the degree of freedom of node all on physical model lower surface is set into constraint, that is, set each node x,
Y, the translational degree of freedom on the directions z is zero, while being also all set to zero around x, y, z axis rotational freedom.
Preferably：Uniform load is applied to physical model upper surface；It selects application nodal force appropriate, uniform load and refers to
Positioning moves.
Preferably：Apply applying load time-division multiple load steps, in 12 load in the upper surface of the structural model point
Step applies compression displacement load, often step compression 0.38mm.
According to specific embodiment provided by the invention, the invention discloses following technique effects：
By the invention it is possible to a kind of warp-knitted spacer fabric composite material stress analysis method be realized, in a kind of realization side
Under formula, this method may include utilizing finite element software, establish the knot of warp-knitted spacer fabric enhancing polyurethane enhancing composite material
Structure model；The parameters of finite element model are set, and the parameter includes that the band yarn mode for being spaced sley bar, each point and band yarn are digital
Paraphysis parameter, warp-knitted spacer fabric enhance compound polyurethane material structural parameters between correspondence, space fabric；According to entity mould
The characteristics of type, carries out mesh generation；Physical model to having divided grid, which applies load and enters post-processing function, generates the warp
Compile the load-deformation curve of space fabric enhancing compound polyurethane material.It will be by method provided by the present application through finite element fraction
It analyses obtained stress-compression ratio curve to be compared with compression test curve, composite material compression stress-pressure of finite element modelling
The compressive deformation curve that shrinkage curve and experiment obtain totally coincide preferably, although stress-pressure of COMPOSITE FINITE ELEMENT simulation
There are a small amount of deviations for shrinkage curve and trial curve, but finite element modelling result provided by the present application still can reflect well
The variation tendency of sample compression performance can provide the theoretical foundation of structure design for the application in Practical Project.
Certainly, it implements any of the products of the present invention and does not necessarily require achieving all the advantages described above at the same time.
Description of the drawings
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the present invention
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached drawings.
Fig. 1 is the flow chart of warp-knitted spacer fabric composite material stress analysis method provided in an embodiment of the present invention；
Fig. 2 is traversing needle gage number -2；
Fig. 3 is traversing needle gage number -3；
Fig. 4 is traversing needle gage number -4；
Fig. 5 is paraphysis global alignment between WSF1；
Fig. 6 is paraphysis global alignment between WSF2；
Fig. 7 is paraphysis global alignment between WSF3；
Fig. 8 is the movement locus for being spaced sley bar GB3；
Fig. 9 is paraphysis physical model between monomer；
Figure 10 is space fabric physical model；
Figure 11 is polyurethane foam physical model；
Figure 12 is composite material represented volume element；
Figure 13 is composite material represented volume element mesh generation；
Figure 14 is compression test curve and finite element modelling curve comparison figure.
Specific implementation mode
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation describes, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, the every other embodiment that those of ordinary skill in the art are obtained belong to what the present invention protected
Range.
Embodiment
Referring to Fig. 1, it is a kind of warp-knitted spacer fabric composite material stress analysis method provided in an embodiment of the present invention, such as schemes
Shown in 1, this method establishes the structure mould of warp-knitted spacer fabric enhancing polyurethane enhancing composite material including the use of finite element software
Type；Specifically, choose a minimum complete loop structure unit be used as represented volume element, the represented volume element for two every
Sley bar a complete band yarn cycle be formed by fabric construction unit and comprising polyurethane foam matrix, to the generation of selection
Table body unit carries out finite element analysis and establishes structural model.
Single paraphysis model is established according to the movement locus every sley bar；Mirror is carried out to single paraphysis physical model successively
Picture, array processing form the 3-D geometric model of paraphysis overall alignment between two interval sley bars；
Establish the upper and lower surface of warp-knitted spacer fabric enhancing compound polyurethane material；
It carries out the 3-D geometric model on established upper and lower surface and paraphysis overall alignment to cohere assembly and be spaced
Fabric substantive model；
Establish a polyurethane foam physical model isometric with space fabric；
Space fabric physical model and polyurethane foam physical model are assembled to get to the structural model.
The single paraphysis method for establishing model include：Initially set up point coordinates A, B, C, D.Then flat in two x-z
In face, straight line tie point A, B and point C, D are used respectively；And in y-z plane, an intermediate point O is selected, with smooth curve by point
B, O is connected with C；Using point A as the center of circle, 0.1mm is that radius does a circle in x-y plane, and this disc is prolonged space curve
ABCD, which is pulled, generates single paraphysis physical model.
The parameters of finite element model are set, and the parameter includes being spaced band yarn mode, each point and the band yarn number of sley bar
Paraphysis parameter, warp-knitted spacer fabric enhance compound polyurethane material structural parameters between code correspondence, space fabric；
According to carrying out mesh generation the characteristics of physical model；Grid is carried out using free mesh in finite element software to draw
Point；Physical model surface mesh thickness, quality, physical grid type parameter are set, using grid Core Generator, to entity mould
Type carries out mesh generation.One end of the physical model is constrained, the other end applies compressive load to realize；On physical model
When being compressed on the directions z of surface, the degree of freedom of node all on physical model lower surface is set into constraint, that is, sets each section
Translational degree of freedom on the x, y, z direction of point is zero, while being also all set to zero around x, y, z axis rotational freedom.To reality
Body Model upper surface applies uniform load；Select application nodal force, uniform load and designated displacement appropriate.When applying load
Multiple load steps are divided to apply, in the load step application compression displacement load of the upper surface of the structural model point 12, often step compression
0.38mm。
Physical model to having divided grid, which applies load and enters post-processing function, generates the warp-knitted spacer fabric increasing
The load-deformation curve of strong compound polyurethane material.
In order to further illustrate scheme provided by the present application, illustrated below by specific example：
The analysis calculating process of ANSYS finite element analysis softwares can be broadly divided into three steps：It pre-treatment, loaded load and asks
Solution post-processing.Pretreatment process include establish analysis object physical model, be arranged finite element model parameters (including meter
Calculate type, cell type and material characteristic parameter etc.), then according to carrying out mesh generation the characteristics of physical model.To dividing
The physical model of grid, so that it may to apply load to it and read out result of calculation into post-processing function.
The application establishes physical model to composite material and applies pressure loading solution.For composite sample,
Required basic geometric parameters are as follows in its modeling process：
The band yarn mode of the intervals fabric WSF1, WSF2 and WSF3 sley bar is respectively：GB3：1-0,2-1/2-1,1-0//,
GB4：2-1,1-0/1-0,2-1//；GB3：1-0,3-2/3-2,1-0//, GB4：3-2,1-0/1-0,3-2//；GB3：1-0,4-
, 1-0//, GB4：4-3,1-0/1-0,4-3//, corresponding gauze pad motion diagram such as Fig. 2, Fig. 3, Fig. 4, Fig. 5, Fig. 6,
Shown in Fig. 7.
1 each point of table and band yarn number correspondence
| Fabric is numbered | A | A' | B | B' | C | C' | D | D' |
| WSF1 | 1-0 | 2-1 | 2-1 | 1-0 | 2-1 | 1-0 | 1-0 | 2-1 |
| WSF2 | 1-0 | 3-2 | 3-2 | 1-0 | 3-2 | 1-0 | 1-0 | 3-2 |
| WSF3 | 1-0 | 4-3 | 4-3 | 1-0 | 4-3 | 1-0 | 1-0 | 4-3 |
Paraphysis parameter between 2 space fabric of table
3 warp-knitted spacer fabric of table enhances compound polyurethane material structural parameters
According to geometric parameter, a minimum complete loop structure unit is chosen as represented volume element, that is, is spaced sley bar
GB3 and GB4 a complete band yarn cycle be formed by fabric construction unit and comprising polyurethane foam matrix, to choosing
Represented volume element carry out finite element analysis.
Paraphysis mould between an a diameter of 0.2mm is established according to the movement locus of the interval sley bar GB3 of sample such as Fig. 8 first
Type, as shown in Figure 9.
Single paraphysis model foundation process：Initially set up point coordinates A (0,0,7.76), B (2.82,0,0), C (2.82 ,-
1,7.76),D(0,-1,0).Then in two x-z-planes, straight line tie point A, B and point C, D are used respectively；And in y-z plane
It is interior, an intermediate point O (2.82, -0.3,3.88) is selected, is connected point B, O with C with smooth curve, to simulate actual interval
Silk curvature of space form.Using point A as the center of circle, 0.1mm is that radius does a circle in x-y plane, and this disc is prolonged space song
Line ABCD pulls paraphysis physical model between generation.
The operations such as " mirror image ", " array " are carried out to single paraphysis physical model successively, formed two interval sley bar GB3 and
The 3-D geometric model of paraphysis overall alignment between GB4.Next the upper and lower surface of space fabric will be established.According to existing
Literature research shows that the compression property of space fabric is mainly determined that pole occurs in compression process for superficial layer by elastic core material
Small deformation influences final result smaller.Therefore, in order to simplify the convergence of difficulty in computation and guarantee model, the application is being spaced
During the foundation of Fabric substantive model, the upper and lower surface of fabric is reduced to entity panel.According to the actual measurement to space fabric
The thickness that fabric upper and lower panel can be obtained is 0.7mm.A block is established with (0,0,7.06) and (2.82, -1,7.76) at 2 points,
That is the upper surface of fabric.It needs to subtract volume Chong Die with paraphysis in the block of upper surface herein, with dummy spacers silk upper
Situation is worn in surface coils.Using same method, the lower surface of fabric is established.By established upper and lower surface and
Paraphysis model, which carries out cohering assembly, obtains space fabric physical model, as shown in Figure 10.
Next a polyurethane foam model isometric with space fabric is established, in order to ensure computational accuracy, poly- ammonia
Ester bubbles model need subtract be distributed in its volume between paraphysis volume, as shown in figure 11.
Finally, it by space fabric physical model and eliminates the polyurethane foam physical model of a paraphysis and assembles, obtain
To composite material represented volume element model, as shown in figure 12.
Definition unit and material properties
According to the own characteristic of composite material model in the application, in conjunction with finite element analysis principle, in mechanical analysis pair
Model uses 10 node of SOLID, 92 analytic unit types.
In terms of the definition of material properties, in composite material represented volume element polyurethane foam matrix, panel and
Paraphysis is defined respectively.Constitutive relation is defined as isotropic elastic body, but its in nonlinear polyurethane matrix material
Constitutive relation is in non-linear.For the panel of composite material, actually impregnated of the space fabric panel of polyurethane foam,
It can be regarded as unidirectional composite material, theoretically there is the horizontal sight same sex, therefore panel can be defined as orthotropy
Body.Between paraphysis it is similar with polyurethane foamed material, be likewise defined as non-linear orthogonal isotropic material.
Polyurethane foam and interval wire material attribute definition
Include to the required parameter of the definition of non-linear isotropic material：Tensile modulus of elasticity, Poisson's ratio, stretching are answered
Stress-strain relationship and bulk density.Former three can get by the extension test to material, and the bulk density of material can also lead to
Drainage is crossed to be calculated.Polyurethane foam and each parameter of paraphysis are as shown in table 4, and wherein E is elasticity modulus of materials, and μ is
The Poisson's ratio of material, ρ are material volume density.
4 polyurethane foam of table and each parameter of paraphysis
5 polyurethane foamed material stress-strain relation of table
| It strains (%) | Stress (MPa) | It strains (%) | Stress (MPa) |
| 0 | 0 | 100 | 0.148 |
| 20 | 0.041 | 120 | 0.158 |
| 40 | 0.079 | 140 | 0.164 |
| 60 | 0.106 | 145 | 0.166 |
| 80 | 0.131 | 153 | 0.169 |
6 paraphysis stress-strain relations of table
| It strains (%) | Stress (GPa) | It strains (%) | Stress (GPa) |
| 0 | 0 | 9.41556 | 1.577 |
| 1.04426 | 0.323 | 11.60292 | 1.933 |
| 3.06833 | 0.66 | 13.62699 | 2.306 |
| 4.76579 | 0.811 | 15.65105 | 2.737 |
| 7.44736 | 1.165 | 17.46025 | 3.112 |
Composite material face material properties define
Since reinforcement space fabric and polyurethane foam matrix use herein do not have in the material depot of software
Definition, it is therefore desirable to by user's self-defining.By preceding described, composite material face can be considered as infiltrated polyurethane foam between
Every fabric panel, it is theoretically equivalent to unidirectional composite material, thus its Engineering Elastic Constants can use unidirectional composite material elasticity
Parameter estimation formula acquires.
To having to obtain the engineered elastomeric of space fabric panel before the solution of composite material face engineered elastomeric parameter
Parameter.For this purpose, upper and lower surface is splitted warp-knitted spacer fabric sample WSF2 along wall by the application, and remove cohere it is upper,
Paraphysis between lower surface.Extension test is carried out to the woven of gained to solve its elastic parameter, the elasticity ginseng of woven
For number result of calculation as shown in table 6-4, wherein E is elasticity modulus of materials (MPa), and G is material modulus of shearing (MPa), and μ is material
Poisson's ratio, subscript 1 indicate the stringer direction of space fabric, and 2 indicate the row direction of space fabric, and 3 indicate flat perpendicular to 1 and 2
Face direction.
The elastic parameter of 7 woven of table
| Material | E1 | E2 | E3 | G12 | G23 | G13 | 12 | 23 | 13 |
| Woven panel | 11.77* | 5.83* | 5.83 | 3.96* | 2.25 | 3.96 | 0.35* | 0.3* | 0.35 |
* it is to be measured by experiment.
Currently, the theoretical formula of estimation unidirectional composite material elastic parameter has very much, the application is according to warp-knitted spacer fabric
The characteristic of reinforcement and polyurethane matrix material has chosen following formula：
Ex=(1-Vf)E1+VfEf
Ey=Ez=EfE2/((1-Vf)E2+VfEf)
Gxy=Gxz=GfG12/((1-Vf)Gf+VfG12)
vxy=vxz=(1-Vf)μ12+Vfvf
vyx=vxyEy/Ex
vyz=(1-Vf)μ23+Vf(2vf-μ23)
Wherein, Ex, Ey, Ez, Gxy, Gxz, Gyz, vxy, vyx and vyz are composite material face elastic parameter, and E1 is single layer
Fabric is along warp direction elasticity modulus, and E2 is woven along weft direction elasticity modulus, and G12, G23 are that woven shears mould
Amount, Ef are matrix elastic modulus, and Gf is matrix modulus of shearing, and μ 12,23 is the Poisson's ratio of woven, and ν f are the Poisson of matrix
Than Vf is matrix material content.
The volume content of polyurethane foam matrix (can be knitted at interval by subtracting dacron thread with the total volume of composite material
Object) volume content determine.The determination method of the volume content of space fabric is as follows in composite material：Calculate space fabric
The terylene thickness of (i.e. gapless) after melting, then can be obtained composite wood with the thickness of obtained terylene thickness divided by composite material
The volume content of dacron thread in material.The calculation formula of dacron thread volume content is：
In formula, Vs-y is dacron thread volume content, and ρ S are the surface density (g/m2) of space fabric, and ρ P are the volume of dacron thread
Density (g/m3), hS are single layer space fabric thickness (mm).
The surface density and thickness of woven measure respectively by experiment：390.84g/m2 and 0.7mm, the body of dacron thread
Product density is 1.38g/m3, and the volume content that woven is calculated according to formula (6-2) is 40.4%, then composite material face
Middle matrix material content is 59.6%.Elastic parameter according to formula (6-1) composite material face is：
Ex=4.78MPa Ey=Ez=0.31MPa
Gyz=0.058MPa Gxy=Gxz=0.076MPa
Vxy=0.32 vyx=0.2 vyz=0.3
Represented volume element mesh generation
Continuous entirety is exactly separated into subregion by the core of finite element method, i.e., it is aforementioned in unit.Therefore net
The quality that lattice divide has apparent influence to result of finite element.Mesh generation density degree also determines to calculate institute indirectly simultaneously
With time and required memory size.In general, mesh generation is smaller, and element number is more in model, when required calculating
Between it is also longer.
This paper uses free mesh in software to carry out mesh generation.Set model surface grid thickness, quality,
The parameters such as physical grid type carry out composite material represented volume element on the model after mesh generation using grid Core Generator
As shown in figure 13.Composite material model is divided using tetrahedron element.Contain in sample after the model partition grid
14597 units.
Apply boundary condition and load
Compression analysis to composite material represented volume element model is to simulate the compression test of sample, by by model
One end constrains, and the other end applies compressive load to realize.When being compressed on the directions composite material z, will own on model lower surface
Node degree of freedom setting constraint, that is, it is zero to set the translational degree of freedom on the x, y, z direction of each node, at the same around
X, y, z axis rotational freedom is also all set to zero.
Uniform load is applied to model upper surface.It can select to apply nodal force, uniform load and designated displacement.The application
It selects to apply designated displacement to the upper surface of model.By compression test result it is found that the compression curve of sample is in nonlinear change
Change, therefore, needs a point multiple load steps to apply when applying load, in the hope of accurately solving.Therefore in the upper surface of finite element model
12 load steps are divided to apply compression displacement load, often step compression 0.38mm.
Stress-compression ratio the curve and compression test curve that will be obtained through finite element analysis by method provided by the present application
It is compared, as a result as shown in figure 14.As seen from Figure 14, the composite material compression stress of finite element modelling-compression ratio is bent
The compressive deformation curve that line and experiment obtain totally coincide preferably, but there are a small amount of deviations, this is primarily due to：In finite element fraction
During analysis, composite material is assumed to be ideal elastomer, and Hooke's law is deferred in its deformation completely, and has ignored poly- ammonia
Friction between ester foam and paraphysis, in actual compression process, the compressive deformation of composite material material not fully takes
Friction from Hooke's law, and between polyurethane foam and paraphysis is also objective reality.Although COMPOSITE FINITE ELEMENT
There are a small amount of deviations for the stress of simulation-compression ratio curve and trial curve, but apply for the finite element modelling result provided still
Can reflect the variation tendency of sample compression performance well, can be provided for the application in Practical Project structure design it is theoretical according to
According to.
Paraphysis needle back the structural parameters of warp-knitted spacer fabric have apparent influence to the energy absorption of composite material
The composite material that traversing number is larger, paraphysis is larger compared with thin, thickness, has higher energy absorption under the conditions of small stress value
Rate is conversely, the composite material that the traversing number of paraphysis needle back is smaller, paraphysis is relatively thick, thickness is smaller is more suitable in big stress condition
It is lower that energy absorbing material is used as to use therefore, it, can be by adjusting the method for fabric construction parameters in actual engineer application
The polyurethane composite material of different-energy absorbent properties is obtained, to meet different application demands
It should be noted that in this application, relational terms such as first and second and the like are used merely to one
Entity or operation are distinguished with another entity or operation, without necessarily requiring or implying between these entities or operation
There are any actual relationship or orders.Moreover, the terms "include", "comprise" or its any other variant are intended to contain
Lid non-exclusive inclusion, so that the process, method, article or equipment including a series of elements is not only wanted including those
Element, but also include other elements that are not explicitly listed, or further include for this process, method, article or equipment
Intrinsic element.In the absence of more restrictions, the element limited by sentence "including a ...", it is not excluded that
There is also other identical elements in process, method, article or equipment including the element.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the scope of the present invention.It is all
Any modification, equivalent replacement, improvement and so within the spirit and principles in the present invention, are all contained in protection scope of the present invention
It is interior.
Claims (8)
1. a kind of warp-knitted spacer fabric composite material stress analysis method, which is characterized in that the method includes：Utilize finite element
Software establishes the structural model of warp-knitted spacer fabric enhancing polyurethane enhancing composite material；Every ginseng of finite element model is set
Number, the parameter include be spaced paraphysis parameter between the band yarn mode of sley bar, each point and band yarn number correspondence, space fabric,
Warp-knitted spacer fabric enhances compound polyurethane material structural parameters；According to carrying out mesh generation the characteristics of physical model；To dividing
The physical model of good grid, which applies load and enters post-processing function, generates the warp-knitted spacer fabric enhancing polyurethane composite
The load-deformation curve of material.
2. warp-knitted spacer fabric composite material stress analysis method according to claim 1, which is characterized in that establish warp knit
Space fabric enhances the structural model of polyurethane enhancing composite material, including：Choose a minimum complete loop structure unit
As represented volume element, the represented volume element is two and is formed by fabric construction list in a complete band yarn cycle every sley bar
Member and comprising polyurethane foam matrix, finite element analysis is carried out to the represented volume element of selection and establishes structural model.
3. warp-knitted spacer fabric composite material stress analysis method according to claim 2, which is characterized in that according to every comb
The movement locus of comb establishes single paraphysis model；Mirror image, array processing are carried out to single paraphysis physical model successively, formed
The 3-D geometric model of paraphysis overall alignment between two interval sley bars；Establish warp-knitted spacer fabric enhancing compound polyurethane material
Upper and lower surface；It carries out the 3-D geometric model on established upper and lower surface and paraphysis overall alignment to cohere assembly and obtain
Space fabric physical model；Establish a polyurethane foam physical model isometric with space fabric；By space fabric entity
Model and polyurethane foam physical model are assembled to get to the structural model.
4. warp-knitted spacer fabric composite material stress analysis method according to claim 3, which is characterized in that described single
Between paraphysis method for establishing model include：Initially set up point coordinates A, B, C, D；Then it in two x-z-planes, uses respectively straight
Line connection point A, B and point C, D；And in y-z plane, an intermediate point O is selected, is connected point B, O with C with smooth curve；With
Point A is the center of circle, and 0.1 mm is that radius does a circle in x-y plane, and this disc is prolonged space curve ABCD and pulls generation list
Paraphysis physical model between root.
5. warp-knitted spacer fabric composite material stress analysis method according to claim 1, which is characterized in that according to entity
The characteristics of model, carries out mesh generation；Including：Mesh generation is carried out using free mesh in finite element software；Set reality
Body Model surface mesh thickness, quality, physical grid type parameter carry out grid using grid Core Generator to physical model
It divides.
6. warp-knitted spacer fabric composite material stress analysis method according to claim 1, which is characterized in that dividing
The physical model of grid applies load, including：One end of the physical model is constrained, the other end, which applies compressive load, to be come in fact
It is existing；When being compressed on the directions z of physical model upper surface, about by the degree of freedom setting of node all on physical model lower surface
Beam, that is, it is zero to set the translational degree of freedom on the x, y, z direction of each node, while around x, y, z axis rotational freedom
It is all set to zero.
7. warp-knitted spacer fabric composite material stress analysis method according to claim 6, which is characterized in that entity mould
Type upper surface applies uniform load；Select application nodal force, uniform load and designated displacement appropriate.
8. warp-knitted spacer fabric composite material stress analysis method according to claim 7, which is characterized in that carried applying
The lotus time-division, multiple load steps applied, and the upper surface of the structural model point 12, load step applies compression displacement load, often walks
Compress 0.38 mm.
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