CN103345545A - Method for predicating composite material Pi-shaped non-planar glue joint strength based on triangular envelopes - Google Patents
Method for predicating composite material Pi-shaped non-planar glue joint strength based on triangular envelopes Download PDFInfo
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Abstract
The invention relates to a method for predicating composite material Pi-shaped non-planar glue joint strength based on triangular envelopes. The method includes the following steps that (1), according to parameters of a composite material Pi-shaped non-planar glue joint structure, a geometrical model is established; (2), according to actual working conditions of the composite material structure, loads and boundary conditions of the Pi joint geometrical model are determined; (3), grid partition is performed on the joint geometrical model, and a Pi joint three-dimensional finite element model is obtained; (4), on the basis of the Pi joint three-dimensional finite element model, a finite element stress analysis is performed; (5), according to the linear finite element stress analysis result, a curved edge triangular envelope route of a Pi negative moment steel padding region is set on the basis of the Pi joint three-dimensional finite element model, all stress component values on the curved edge triangular envelope route are extracted, and the average value of the stress component values is calculated and substituted to the failure criterion for predicating the strength. The method for predicating the composite material Pi-shaped non-planar glue joint strength based on the triangular envelopes is suitable for engineering application and can obviously shorten a development cycle and reduce experimentation cost.
Description
Technical field
The present invention relates to integration composite structure typical case on-plane surface and glued joint the prediction of strength that connects, be applicable to that widely used complex composite material on-plane surface glueds joint syndeton in the aerospace flight vehicle.
Background technology
Compound substance is because of its high specific strength, high specific stiffness and can cut out good characteristics such as design and be widely used in the aerospace flight vehicle structure.It is link efficiently in the integration composite structure that adhesive bonding of composites connects, splicing is connected with on-plane surface to be divided into plane splicing connection, wherein on-plane surface glued joint to connect owing to can transmit the plane external applied load, realize having certain angle composite element connection and be applied in the complex composite material structure.Yet syndeton also is the key position that determines composite structure intensity, and researchers have carried out number of research projects at glueing joint to connect for this reason.
Connect complex structure for connection is gluedd joint on the plane because on-plane surface glueds joint, adopt theoretical analysis method and linear finite analytical approach to measure the intensity difficulty.The main method prediction strength of joints such as progressive damage method, virtual crack closure techniques and cohesion model of using of present researchers, adopt these methods to carry out prediction of strength and need constantly to detect composite structure damage or crackle extended mode, and carry out non linear finite element analysis again to obtain the load/stress level of redistribution according to the current state of composite structure, and estimate, the calculating scale is big, computing time is long, is not suitable for engineering and uses.Therefore during engineering is used, can only rely on a large amount of tests and determine that complex composite material on-plane surface glueds joint the intensity that connects, the lead time is long, cost is high.
Summary of the invention
Technology of the present invention is dealt with problems: overcome the deficiencies in the prior art, provide a kind of compound substance π shape on-plane surface based on the triangle envelope to glued joint the strength of joint Forecasting Methodology, be applicable to the engineering application, can significantly shorten the lead time, reduce experimentation cost.
Technical solution of the present invention: a kind of compound substance π shape on-plane surface based on the triangle envelope glueds joint the strength of joint Forecasting Methodology, and performing step is as follows:
Steps A is utilized finite element software d solid modeling function, glueds joint the syndeton parameter according to compound substance π shape on-plane surface and sets up π joint geometric model;
Step B according to the actual condition of composite structure, determines that compound substance π shape on-plane surface glueds joint load and the boundary condition of syndeton, is applied to this load and boundary condition on the π joint geometric model;
Step C to covering, web and the grouping of π reinforcement of π joint geometric model, divides grid by the grid requirement of each group, obtains π joint three-dimensional finite element model;
Step D, based on π joint three-dimensional finite element model, load and boundary condition according to step B determines utilize finite element software to carry out the linear stress analysis, calculate the stress distribution of π joint under this load and boundary condition;
Step e, after drawing the stress distribution of π joint under specified load and boundary condition, in π joint three-dimensional finite element model bent limit, π reinforcement packing area triangle envelope depth is set, extract each components of stress value of each gusset material principal direction on this song limit triangle envelope depth, calculate each components of stress mean value, the corresponding expression formula of substitution failure criteria is found out and is had peaked expression formula, calculate the load value that this expression formula equals 1 o'clock correspondence, i.e. π strength of joint value.
Setting up the geometric model implementation procedure according to compound substance π shape on-plane surface splicing syndeton parameter in the described steps A is:
(A1) according to concrete compound substance π joint design parameter value, draw π joint geometric profile figure at two dimensional surface, by the entity stretching mode, broad ways stretching developed width value is set up π joint 3-D geometric model;
(A2) definition material properties and local material direction, and by each shop layer thickness value division geometric model, create compound material laying layer and definition shop layer angle, when the layer angle of definition shop, need set up corresponding local coordinate system according to actual conditions.
Described step B determines that according to the actual condition of composite structure the load of π joint geometric model and boundary condition implementation procedure are:
(B1) composite structure is carried out force analysis, determine that π shape on-plane surface glueds joint restraint condition and the suffered tensile load of syndeton;
(B2) top restraint condition is put on the π joint geometric model as boundary condition, simultaneously the resulting tensile load of force analysis on π joint geometric model applies.
The detailed process that described step C divides grid based on π joint geometric model is:
(C1) along the even cloth kind of three directions of length of covering and web, and divide grid, this grid does not need very meticulous;
(C2) along the even cloth kind of three directions of length of π reinforcement, and divide grid, this grid is meticulousr than the grid of covering and web;
(C3) progressively encrypt π reinforcement packing area grid, whole finite element model is carried out Stress calculation, the stress solution until obtaining convergence just obtains π joint three-dimensional finite element model.
Described step e according to the specific implementation process of finite element stress analysis prediction of result π strength of joint is:
(E1) utilize the post-processing function of finite element software, in π joint three-dimensional finite element model as shown in Figure 2 bent limit, π reinforcement packing area triangle envelope depth is set, and extract each components of stress value of each gusset material principal direction on this song limit triangle envelope depth;
(E2) calculate each components of stress mean value, the corresponding expression formula of substitution failure criteria is found out and is had peaked expression formula;
(E3) calculate the load value that this expression formula equals 1 o'clock correspondence, i.e. π strength of joint value.
The present invention's advantage compared with prior art is:
(1) the compound substance π shape on-plane surface that the present invention is based on the triangle envelope glueds joint the strength of joint Forecasting Methodology, utilizes the modern computer powerful computing ability, calculates π joint stress distribution and predicted intensity by three dimensional FEM simulation.Through showing to predict the outcome to have good consistance with test findings with comparison of test results, guaranteed precision of prediction.
(2) the compound substance π shape on-plane surface that the present invention is based on the triangle envelope glueds joint the strength of joint Forecasting Methodology, only need carry out the linear finite analysis is measurable π joint ultimate failure intensity, simplified the finite element simulation calculation process greatly, saved and assessed the cost and the time, be applicable to the π strength of joint prediction in the engineering application, can significantly shorten the lead time, reduce experimentation cost.
Description of drawings
Fig. 1 is realization flow figure of the present invention;
Fig. 2 is the bent limit triangle envelope that the present invention proposes.
Embodiment
As shown in Figure 1, the inventive method specific implementation is:
1. glued joint the syndeton parameter according to compound substance π shape on-plane surface and set up π joint geometric model.
Utilize finite element software d solid modeling function, glued joint the syndeton parameter value according to compound substance π shape on-plane surface, draw π joint geometric profile figure at two dimensional surface, by the entity stretching mode, broad ways stretching developed width value is set up π joint geometric model; Definition material properties and local material direction, and by each shop layer thickness value division π joint geometric model, create compound material laying layer and definition shop layer angle, when the layer angle of definition shop, need set up corresponding local coordinate system according to actual conditions.
2. determine load and the boundary condition of π joint geometric model according to the actual condition of composite structure.
Composite structure is carried out force analysis, determine that π shape on-plane surface glueds joint restraint condition and the suffered tensile load of syndeton; Restraint condition is put on the π joint geometric model as boundary condition, apply the resulting tensile load of force analysis at π joint geometric model simultaneously.
3. divide grid based on π joint geometric model.
To covering, web and the grouping of π reinforcement of π joint geometric model, divide grid by the grid requirement of each group, along the even cloth kind of three directions of length of covering and web, and divide grid, this grid does not need very meticulous; Along the even cloth kind of three directions of length of π reinforcement, and divide grid, this grid is meticulousr than the grid of covering and web; Progressively encrypt π reinforcement packing area grid, and whole finite element model is carried out Stress calculation, the stress solution until obtaining convergence just obtains π joint three-dimensional finite element model.
4. carry out finite element stress analysis based on π joint three-dimensional finite element model.
Based on π joint three-dimensional finite element model, carry out the linear finite stress analysis, calculate π joint given load and the stress distribution under the boundary condition in the above.
5. according to finite element stress analysis prediction of result π strength of joint.
After obtaining the stress distribution of π joint under specified load and boundary condition, utilize the post-processing function of finite element software, at bent limit, π joint three-dimensional finite element model setting π reinforcement packing area as shown in Figure 2 triangle envelope, extract each components of stress value of each gusset material principal direction on this song limit triangle envelope depth, calculate each components of stress mean value, the corresponding expression formula of substitution failure criteria, find out and have peaked expression formula, calculate the load value that this expression formula equals 1 o'clock correspondence, i.e. π strength of joint value.
Embodiment 1: compound substance π shape on-plane surface glueds joint the strength of joint prediction
1. geometric description:
Compound substance π shape on-plane surface glueds joint the long 200mm of syndeton, high 160mm, wide 50mm, be divided into covering, web and three parts of π reinforcement, the π reinforcement comprises L shop layer, U shop layer, shape shop layer and packing area, and each several part utilizes the tackifier perfect adhesion, and material is T700/QY8911.
(1) shop layer about web: [0 °/0 °/45 °/-45 °]
s, thickness respectively is 1mm;
(2) covering two-berth layer: [45 °/90 °/-45 °/0 °]
s, thickness respectively is 1mm;
(3) π reinforcement shop layer: L layer and U layer are [45 °/90 °/-45 °], and a shape layer is [45 °/90 °/45 °], and thickness respectively is 0.36mm, and filler is 0 ° of one-way tape, and 0 ° of direction is along π weld width direction.
2. finite element model is set up and prediction of strength:
Steps A, glued joint the syndeton parameter according to top given compound substance π shape on-plane surface and set up π joint geometric model, the definition material properties, divide geometric model according to each shop layer thickness, give material properties and shop layer angle for each shop layer, when creating shop layer angle, set up 6 local coordinate systems;
Step B, glued joint the stressed and support situation of syndeton according to compound substance π shape on-plane surface, determine load and the boundary condition of π joint geometric model, load in the present embodiment 1 and boundary condition and π joint tensile strength tester for testing are consistent, all degree of freedom of the covering both ends of the surface node of constraint π joint geometric model and covering be apart from the degree of freedom of the upper surface node y direction of each 20mm of both ends of the surface, and apply equally distributed tensile load at the web upper surface of π joint geometric model;
Step C, divide grid based on π joint geometric model, for covering and web, do not need very meticulous grid, and the π reinforcement is the key of transmitted load, need meticulous grid, so earlier to covering and web along the even cloth kind of three directions of length and divide grid, again the π reinforcement is divided meticulousr grid in an identical manner.To π reinforcement packing area, need progressively refined net, the line linearity finite element stress analysis of going forward side by side, the stress solution until obtaining convergence just obtains π joint three-dimensional finite element model;
Step D, in π joint three-dimensional finite element model as shown in Figure 2 bent limit, π reinforcement packing area triangle envelope is set, extract each components of stress value of each gusset material principal direction on this song limit triangle envelope depth, calculate each components of stress mean value, substitution maximum stress criterion prediction π strength of joint, predicting the outcome has good consistance with test findings.Concrete computation process is as follows:
The maximum stress criterion thinks that individual layer namely destroyed when a certain positive axis components of stress of individual layer value reached its intensity values corresponding, and its expression formula can be written as:
Wherein, σ
11Be the normal stress component of individual layer along machine direction, σ
22Be the normal stress component of individual layer perpendicular to machine direction, σ
33Be the normal stress component of thickness in monolayer direction, τ
12Be the single flat inplane shear components of stress, τ
13And τ
23Be the individual layer interlayer shear components of stress; X
T, cBe stretching or the compression strenght of individual layer along machine direction, Y
T, cBe stretching or the compression strenght of individual layer perpendicular to machine direction, Z
T, cBe stretching or the compression strenght of thickness in monolayer direction, S
12Be single flat inplane shear intensity, S
13And S
23Be individual layer interlayer lateral shear intensity.
Each components of stress mean value substitution following formula of each gusset material principal direction calculates the stress value that satisfies following formula on the triangle envelope depth of bent limit, the π reinforcement packing area that the linear finite stress analysis is obtained, and the load value of this stress value correspondence is π strength of joint value.
The non-elaborated part of the present invention belongs to those skilled in the art's known technology.
Claims (5)
1. the compound substance π shape on-plane surface based on the triangle envelope glueds joint the strength of joint Forecasting Methodology, it is characterized in that may further comprise the steps:
Steps A is utilized finite element software d solid modeling function, glueds joint the syndeton parameter according to compound substance π shape on-plane surface and sets up π joint geometric model, provides geometric configuration for setting up π joint three-dimensional finite element model;
Step B according to the actual condition of composite structure, determines that compound substance π shape on-plane surface glueds joint load and the boundary condition of syndeton, and this load and boundary condition are applied on the π joint geometric model, is convenient to carry out stress analysis;
Step C to covering, web and the grouping of π reinforcement of π joint geometric model, divides grid by the grid requirement of each group, obtains π joint three-dimensional finite element model;
Step D, based on π joint three-dimensional finite element model, load and boundary condition according to step B determines carry out the linear finite stress analysis, calculate π joint stress distribution;
Step e, after drawing the stress distribution of π joint under specified load and boundary condition, in π joint three-dimensional finite element model bent limit, π reinforcement packing area triangle envelope depth is set, extract each components of stress value of each gusset material principal direction on this song limit triangle envelope depth, get the corresponding expression formula of each components of stress mean value substitution failure criteria, find out and have peaked expression formula, calculate the load value that this expression formula equals at 1 o'clock, i.e. π strength of joint value.
2. a kind of compound substance π shape on-plane surface based on the triangle envelope according to claim 1 glueds joint the strength of joint Forecasting Methodology, it is characterized in that: setting up the geometric model implementation procedure according to compound substance π shape on-plane surface splicing syndeton parameter in the described steps A is:
(A1) glued joint the syndeton parameter value according to concrete compound substance π shape on-plane surface, draw π joint geometric profile figure at two dimensional surface, by the entity stretching mode, broad ways stretching developed width value is set up π joint geometric model;
(A2) definition material properties and local material direction, and by each shop layer thickness value division geometric model, create compound material laying layer and definition shop layer angle, when the layer angle of definition shop, need set up corresponding local coordinate system according to actual conditions.
3. a kind of compound substance π shape on-plane surface based on the triangle envelope according to claim 1 glueds joint the strength of joint Forecasting Methodology, it is characterized in that: described step B determines that according to the actual condition of composite structure the load of π joint geometric model and boundary condition implementation procedure are:
(B1) composite structure is carried out force analysis, determine that π shape on-plane surface glueds joint restraint condition and the suffered tensile load of syndeton;
(B2) top restraint condition is put on the π joint geometric model as boundary condition, simultaneously the resulting tensile load of force analysis on π joint geometric model applies.
4. a kind of compound substance π shape on-plane surface based on the triangle envelope according to claim 1 glueds joint the strength of joint Forecasting Methodology, and it is characterized in that: the detailed process that described step C divides grid based on π joint geometric model is:
(C1) along the even cloth kind of three directions of length of covering and web, and divide grid;
(C2) along the even cloth kind of three directions of length of π reinforcement, and divide grid;
(C3) progressively encrypt π reinforcement packing area grid, π joint three-dimensional finite element model is carried out linear stress calculate, the stress solution until obtaining convergence just obtains π joint three-dimensional finite element model.
5. a kind of compound substance π shape on-plane surface based on the triangle envelope according to claim 1 glueds joint the strength of joint Forecasting Methodology, and it is characterized in that: described step e according to the specific implementation process of finite element stress analysis prediction of result π strength of joint is:
(E1) utilize the post-processing function of finite element software, based on π joint three-dimensional finite element model bent limit, π reinforcement packing area triangle envelope depth is set, and extract each components of stress value of each gusset material principal direction on this song limit triangle envelope depth;
(E2) calculate each components of stress mean value, the corresponding expression formula of substitution failure criteria is found out and is had peaked expression formula;
(E3) calculate the load value that this expression formula equals 1 o'clock correspondence, i.e. π strength of joint value.
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102521435A (en) * | 2011-11-29 | 2012-06-27 | 苏州大学 | Laminating manufacture method for symmetric laminated plate |
-
2013
- 2013-06-14 CN CN201310234740.7A patent/CN103345545B/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102521435A (en) * | 2011-11-29 | 2012-06-27 | 苏州大学 | Laminating manufacture method for symmetric laminated plate |
Non-Patent Citations (4)
| Title |
|---|
| ZHANG JIANYU 等: "Mechanics Design of Connecting Frame in Aircraft Composite Cabin", 《ADVANCED MATERIALS RESEARCH》 * |
| ZHAO LIBIN 等: "Strength Prediction of Connecting Frame in Aircraft Composite Cabin", 《ADVANCED MATERIALS RESEARCH》 * |
| 赵丽滨 等: "复合材料_接头拉伸力学性能的试验和计算研究", 《复合材料学报》 * |
| 赵丽滨: "复合材料结构三维有限元分析的材料参数", 《北京航空航天大学学报》 * |
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