CN106626449B - Consider the design method in the composite material V-type component autoclave molding tooling type face of curing deformation - Google Patents
Consider the design method in the composite material V-type component autoclave molding tooling type face of curing deformation Download PDFInfo
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- CN106626449B CN106626449B CN201610985260.8A CN201610985260A CN106626449B CN 106626449 B CN106626449 B CN 106626449B CN 201610985260 A CN201610985260 A CN 201610985260A CN 106626449 B CN106626449 B CN 106626449B
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
- B29C33/3835—Designing moulds, e.g. using CAD-CAM
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
Abstract
The invention discloses a kind of design methods in composite material V-type component autoclave molding tooling type face for considering curing deformation, belong to fibre reinforced composites molding component technical field.The characteristics of present invention is according to autoclave forming process, utilize finite element method, shape after assigning the design shape of V-type component as curing deformation, as calculating primary condition, shape before Converse solved molding component, to obtain the design mode face of tooling, according to the type face, molding component just becomes the design shape of component after forming in autoclave.Do not have to repeatedly trial and error using design method of the present invention to repair a die, reduces the production cost of component, shorten the production cycle, improve the production efficiency and the quality of production of fibre reinforced composites component.
Description
Technical field
The invention belongs to fibre reinforced composites molding component technical field, it is related to a kind of considering the compound of curing deformation
The design method in material V-type component autoclave molding tooling type face.
Background technique
Compared to metal material, the specific strength of fiber-reinforced resin matrix compound material is high, specific modulus is big, corrosion-resistant, to tired
Labor is insensitive, and material property can flexibly design.Based on above-mentioned excellent performance, carbon fiber enhancement resin base composite material is led in aviation
The dosage in domain is increasing, and dosage of the composite material in aircraft has become an important finger of assessment aircraft advance
Mark.
Currently, composite element mainly uses autoclave forming process to manufacture.In the initial stage rank of autoclave molding process
Section, the modulus of fiber-reinforced resin matrix compound material is low, and the residual stress of generation is small.With in autoclave temperature be increased to it is compound
The modulus of the glass transition temperature of material, material rapidly increases.During then, the residual stress that temperature change generates is to lead
The main reason for causing component to be cured deformation.For V-type component, the principal element of curing deformation is the solidification in solidification process
It shrinks and thermally expands.In forming process, material occurs a series of physical-chemical reaction and material properties is constantly become
Change, along with the attribute of fiber-reinforced resin matrix compound material is anisotropy, becomes so that generating solidification after molding component
Shape, last gained shape are different from the design shape of anticipation.This phenomenon increases the assembly difficulty of component, reduces assembly
Efficiency and assembling quality.For the component of aircraft exterior, curing deformation also will affect the aerodynamic configuration of aircraft, and curing deformation is tight
Component is also resulted in when weight to scrap, and is increased manufacturing cost, is extended manufacture cycle.
Traditional countermeasure is to modify the type face of molding component tooling repeatedly using trial-and-error method, i.e. component generates solidification and becomes
After shape, the tooling type face of molding component is modified, manufactures experimently component again, if deformation continues to correct beyond requirement, wanted until meeting
It asks.Trial-and-error method needs repeatedly trial and error to repair a die, and high production cost, the production cycle is long, is unfavorable for the production of composite element.
Summary of the invention
To solve problems of the prior art, the present invention proposes a kind of composite material V-type structure for considering curing deformation
The design method in part autoclave molding tooling type face.The characteristics of present invention is according to autoclave forming process, using finite element method,
The design shape of V-type component as the shape after curing deformation, as calculating primary condition, before Converse solved molding component
Shape, to obtain the design mode face of tooling, according to the type face, molding component just becomes component after forming in autoclave
Design shape.
The present invention proposes a kind of design side in composite material V-type component autoclave molding tooling type face for considering curing deformation
Method, specific step is as follows：
(1) the design shape model of V-type component is established in finite element software；
(2) model partition grid is given according to the design shape aspect of model of the V-type component, and according to actual production
Situation assigns composite plys to model；
(3) according to the boundary condition of the design shape model of the network setting V-type component；
(4) according to the temperature field of the variation setting variation of temperature in composite material solidification process；Due to being the reverse of use
The variation of the mode of solution, temperature field is opposite with the temperature field timing applied in practical solidification process；
(5) it is calculated according to the constitutive relation of material properties change in the temperature field feature and material
Material is because of mechanical stress and thermal expansion bring deformation；
(6) according to the shape that the boundary condition and deformation calculation obtain component it is shape before component curing deformation
Shape, design mode face of the surface as tooling before extracting the deformation of member.
The present invention is a kind of design side in composite material V-type component autoclave molding tooling type face for considering curing deformation
Method, advantages and beneficial effects are：Do not have to repeatedly trial and error using this design method to repair a die, reduces being produced into for component
This, shortens the production cycle, improves the production efficiency and the quality of production of fibre reinforced composites component.
Detailed description of the invention
Fig. 1 is the design method in the composite material V-type component autoclave molding tooling type face that the present invention considers curing deformation
Flow chart；
Fig. 2 is the composite material V-type component model schematic diagram established according to embodiments of the present invention；Wherein, 1 a:1 scaling
Front view, b 1:The left view of 1 scaling, c 1:The isometric side view of 1 scaling；
Fig. 3 is the finite element model figure that grid dividing is carried out to model shown in Fig. 2；
Fig. 4 is the schematic diagram to Fig. 3 finite element model displacement constraint；
Fig. 5 is the temperature sequence figure that composite element is undergone in autoclave；
Fig. 6 is the autoclave temperature that uses of FEM calculation against timing diagram；
Fig. 7 is the Aberration nephogram that composite element inversely calculates；
Fig. 8 is to generate V-type component tooling type face schematic diagram.
Specific embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.
The design side in the composite material V-type component autoclave molding tooling type face of consideration curing deformation of the present invention
Preferably to design a model as the primary condition of calculating shape of the component before curing deformation is inversely calculated, according to change in method
Shape before shape extracts tooling type face, it is ensured that deformed shape is cured in autoclave according to the molding component in tooling type face
Shape is identical as design shape.Holistic approach process of the present invention is as shown in Figure 1, make each step below with reference to embodiment following specific
Explanation：
(1) the design shape model of V-type component is established in finite element software, specially：With composite material corner allusion quotation
For type component, establish in finite element software with a thickness of 3mm, width 20mm, length of straight flange 60mm, corner angle is
60 °, corner radius is the three-dimensional V-type model of the outer 8mm of interior 5mm, as shown in Figure 2.The model is preferably to design a model, in hot pressing
It should be consistent with the model after the molding deformation of member in tank and just be able to satisfy design requirement.
(2) model partition grid is given according to the design shape aspect of model of the V-type component, and according to actual production
Situation assigns composite plys to model.The embodiment of the present invention is specially：To the three-dimensional V-type model partition structuring net
Lattice, and composite plys are assigned to the three-dimensional V-type model according to the actual situation.The laying of example is [- 45/90/
45/0]3S, 24 layers of quasi-isotropic symmetric layups.Mesh shape is as shown in Figure 3.
(3) according to the boundary condition of the design shape model of the network setting V-type component.The embodiment of the present invention
Specially：As shown in figure 4, boundary condition is arranged to the three-dimensional V-type model, four nodes of V-type component one end are constrained, it is right
Displacement on tri- directions joint constraint X, Y, Z of lower left guarantees that space displacement does not occur for component；To upper left side joint constraint
The displacement of X-direction and Y-direction guarantees that component does not occur around Y-axis and around the rotation of X-axis；To the joint constraint Y-direction of lower right and
The displacement of Z-direction guarantees that the rotation with Y-axis about the z axis does not occur for component；To the displacement in the joint constraint Y-direction in upper right side, protect
Rotation about the z axis does not occur for card component.
(4) according to the temperature field of the variation setting variation of temperature in composite material solidification process.The embodiment of the present invention is specific
For：The temperature field timing that composite element is actually undergone in autoclave, as shown in Figure 5；Due to being the Converse solved of use
Mode, the variation in temperature field is opposite with the temperature field timing actually undergone shown in Fig. 5；Therefore to the three-dimensional V-type model
Reverse temperature field is set, and the result inversely calculated is as shown in Figure 6.
(5) sub- journey is write according to the constitutive relation of material properties change in the temperature field feature and material
Sequence, is calculated material because of mechanical stress and thermal expansion bring deformation, that is, completes compound after the solidification process
Material deformation experienced.
The embodiment of the present invention is specially：Fiber-reinforced resin matrix compound material during solidification of hot-press tank, material
An elastic constant not instead of fixed value, changes with the variation of temperature and curing degree.But one it is given very
In small time step, elastic constant can be considered as constant.Therefore, although it cannot be guaranteed that mechanical stress σ=E ε, total
It is able to satisfy d σ=Ed ε, wherein E is the instantaneous modulus of material, and ε is that strain represents deformation, and d ε is represented in the time step of very little
Deformation.
The strain-stress relation of orthotropic material meets ε=S σ, and wherein S is the flexibility matrix of material；Material
Jacobian matrixThe machine direction for defining fiber-reinforced resin matrix compound material is 1 direction, thickness direction
For 3 directions, then 2 directions are the plane constituted perpendicular to 1 direction and 3 directions；By testing or being calculated different moments just
Hand over 9 elastic constants of anisotropic material：E1、E2、E3、v12、v13、v23、G12、G13、G23With the thermal expansion coefficient in 3 directions：
α1、α2、α3；Wherein, E1、E2And E3It is the elasticity modulus in 1 direction of material, 2 directions and 3 directions, v respectively12、v13、v23It is material respectively
Expect the Poisson's ratio in 12 directions, 13 directions and 23 directions, G12、G13、G23It is the shearing mould in 12 directions, 13 directions and 23 directions respectively
Amount, α1、α2、α3The respectively thermal expansion coefficient in 1 direction of material, 2 directions and 3 directions.
Orthotropy flexibility matrix S meets：
The Jacobian matrix J=S of material-1The inverse of flexibility matrix is asked to obtain by subroutine program, Δ σ=J Δ ε, σn+1=
σn+Δσ.The mechanical stress of material is solved can be completed by cumulative.
Similarly, material is because of thermal expansion bring strain ΔεT=α Δ T,Wherein α is thermal expansion system
Number, T represent temperature.
(6) according to the shape that the boundary condition and deformation calculation obtain component it is shape before component curing deformation
Shape, design mode face of the surface as tooling before extracting the deformation of member, specially：As shown in fig. 7, the shape of transparent part is V
Type component is cured deformed shape, i.e. ideal model；Before entity part is the component curing deformation obtained after being computed
Shape, i.e. tooling type face.According to the boundary condition being arranged and the deformation being calculated output V-type structure in finite element software
The node of inner surface or outer surface before part curing deformation produces tooling type face in CATIA 3 d modeling software, such as schemes
Shown in 8.
Through the above steps, according to the molding component in tooling type face generated in the CATIA 3 d modeling software,
Be cured in autoclave deformed shape with preferably design a model it is identical.The method of the embodiment of the present invention is for other
The V-type component of shape is applicable in.
Claims (2)
1. considering the design method in the composite material V-type component autoclave molding tooling type face of curing deformation, it is characterised in that：Packet
Include following steps：
(1) the design shape model of V-type component is established in finite element software；
(2) model partition grid is given according to the design shape aspect of model of the V-type component, and assigns composite wood to model
Expect laying；
(3) according to the boundary condition of the design shape model of the network setting V-type component；
(4) according to the temperature field of the variation setting variation of temperature in composite material solidification process；The variation in temperature field and V-type component
Actually applied temperature field timing is opposite during autoclave molding；
(5) subprogram is write according to the constitutive relation of material properties change in the temperature field feature and material, institute
The subprogram stated is for obtaining the composite material in the solidification process in opposite timing temperature field because of mechanical stress and thermal dilation belt
The deformation come；
(6) according to the shape that the boundary condition and deformation calculation obtain component it is shape before component curing deformation, mentions
Design mode face of the surface as tooling before taking the deformation of member.
2. the composite material V-type component autoclave molding tooling type face according to claim 1 for considering curing deformation is set
Meter method, it is characterised in that：The process for writing subprogram is as follows：The composite material is orthotropy material
Material, strain-stress relation meet ε=S σ, and wherein ε is that strain represents deformation, and S is the flexibility matrix of material, and σ is that machinery is answered
Power；The Jacobian matrix of materialThe machine direction for defining composite material is 1 direction, and thickness direction is 3 sides
To then 2 directions are the plane constituted perpendicular to 1 direction and 3 directions；Different moments orthotropic material is obtained by calculation
9 elastic constants：E1、E2、E3、v12、v13、v23、G12、G13、G23With the thermal expansion coefficient in 3 directions：α1、α2、α3；Wherein,
E1、E2And E3It is the elasticity modulus in 1 direction of material, 2 directions and 3 directions, v respectively12、v13、v23It is 12 direction of material, 13 sides respectively
To the Poisson's ratio with 23 directions, G12、G13、G23It is the modulus of shearing in 12 directions, 13 directions and 23 directions, α respectively1、α2、α3Respectively
For the thermal expansion coefficient in 1 direction of material, 2 directions and 3 directions；
Orthotropy flexibility matrix S meets：
The Jacobian matrix J=S of material-1The inverse of flexibility matrix is asked to obtain by subroutine program, Δ σ=J Δ ε, σn+1=σn+
Δσ；The mechanical stress of material is solved to be obtained by cumulative；
Material is because of thermal expansion bring strain ΔεT=α Δ T,Wherein α is thermal expansion coefficient, and T represents temperature
Degree.
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| CN109492323B (en) * | 2018-11-25 | 2022-02-25 | 南昌航空大学 | High-precision inverse calculation method for initial residual stress of blank based on deformation test |
| CN109501325B (en) * | 2018-12-14 | 2020-08-04 | 北京航空航天大学 | Method and device for predicting curing deformation of composite material member |
| CN109702931B (en) * | 2019-01-30 | 2020-01-24 | 中南大学 | Method for designing mold surface of computer-aided large-scale component precise hot forming mold |
| CN109702930B (en) * | 2019-01-30 | 2020-01-24 | 中南大学 | Solid mold design method for accurate thermal forming of component |
| CN110576621A (en) * | 2019-09-12 | 2019-12-17 | 长春长光宇航复合材料有限公司 | Cyanate ester resin based near-zero expansion composite material truss rod and preparation method thereof |
| CN111331884A (en) * | 2020-03-04 | 2020-06-26 | 中国科学院力学研究所 | Method and device for determining forming die of carbon fiber composite material reflecting surface structure |
| CN112149322B (en) * | 2020-08-21 | 2022-05-10 | 成都飞机工业（集团）有限责任公司 | Finite element analysis method for curing deformation of composite material reinforced structure |
| CN112149324B (en) * | 2020-08-28 | 2022-10-25 | 成都飞机工业（集团）有限责任公司 | Rapid modeling method for simulation verification of composite material tool compensation molded surface |
| CN113607772B (en) * | 2021-08-04 | 2022-09-09 | 西北工业大学 | Method and system for determining damage of toughened composite material during curing molding |
| CN117067633B (en) * | 2023-10-12 | 2024-03-15 | 成都飞机工业（集团）有限责任公司 | Condensing system state monitoring method based on standard condensing curve |
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| CN104441698B (en) * | 2014-12-02 | 2016-07-06 | 大连理工大学 | A kind of method adjusting autoclave flow field temperature homogeneity |
| CN105965841B (en) * | 2016-07-05 | 2017-12-05 | 盐城工学院 | A kind of experimental provision and its experimental method of polymer inverse extrusion die mold desing |
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