CN107885946A - A kind of method based on progressive damage model prediction composite Multi-fasteners joint intensity - Google Patents

A kind of method based on progressive damage model prediction composite Multi-fasteners joint intensity Download PDF

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CN107885946A
CN107885946A CN201711180125.7A CN201711180125A CN107885946A CN 107885946 A CN107885946 A CN 107885946A CN 201711180125 A CN201711180125 A CN 201711180125A CN 107885946 A CN107885946 A CN 107885946A
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composite multi
load
carbon fibre
fasteners joint
fibre composite
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周金宇
孙涛
臧杰
邱睿
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Jiangsu University of Technology
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    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
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    • G06F30/17—Mechanical parametric or variational design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
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    • G06F2119/06—Power analysis or power optimisation

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Abstract

The method of carbon fibre composite Multi-fasteners joint intensity is predicted based on progressive damage model the invention discloses a kind of, step is as follows：(1) geometrical model of carbon fibre composite Multi-fasteners joint is established in ANSYS softwares；(2) pin load distribution analysis is carried out to carbon fibre composite using the FInite Element that pin load distribution calculates, to determine the position in crucial hole；(3) programmed by APDL and obtain perforate laminate tensile failure load and extruding breaking load；(4) stretch characteristic size and compressive features size are calculated according to breaking load；(5) expression formula of classical indicatrix is determined based on resulting compression and stretch characteristic size；(6) according to the intensity and failure mode of obtained expression formula prediction carbon fibre composite Multi-fasteners joint.The present invention not only saves substantial amounts of time and cost, improves the efficiency of structure design, and can accurately predict the intensity and failure mode of Multi-fasteners joint.

Description

A kind of method based on progressive damage model prediction composite Multi-fasteners joint intensity
Technical field
The present invention relates to a kind of method based on progressive damage model prediction composite Multi-fasteners joint intensity.
Background technology
Carbon fibre reinforced composite is using carbon fiber or carbon fibre fabric as reinforcement, is formed using resin by matrix Composite, there is high intensity, high-modulus, low-density.These excellent performances cause it using quite varied.But The structure design of carbon fibre reinforced composite and manufacture are its key application problems, and the connectivity problem of structure is always then to be somebody's turn to do The problem of item technology.The connection of carbon fibre reinforced composite is mainly bolt connection and is glued connection, big in intensity height, load In the case of typically all use bolt connection, and bolt connection also allows for dismantling, so being bolted to composite connection Middle use is quite varied.
Characteristic curve method is a kind of empirical method of mechanical coupling strength prediction.Because apertures side has stress concentration, grind The characteristics of person of studying carefully is by defining the indicatrix on hole side and its corresponding to, and according to the stress state at these characteristic points come the company of evaluation Whether binding structure fails.The characteristic curve method proposed on this basis, this method assume that hole side has an indicatrix, can be with Whether the stress state evaluation bolt connection according to being put on curve fails.Because characteristic curve method is simple and convenient, and have well Precision of prediction, so being widely used in engineering.
Three key elements of characteristic curve method are respectively the form of indicatrix, indicatrix size and failure criteria.The party Method is proposed that its indicatrix form is the curve determined by stretch characteristic length and compressive features length by Chang earliest, Its expression formula is：
rc(θ)=r0+Rt+(Rc-Rt)cosθ-90°≤θ≤90°
In formula, RtAnd RcRespectively stretch characteristic size and compressive features size, determined by experiment；r0For the radius in hole；θ The angle rotated clockwise or counterclockwise to drawing plane direction for the longitudinal direction extruding plane of composite connection.Attachment structure Failure mode divides according to θ position：When 0 °≤| θ | be compression failure at≤15 °；30 °≤| θ | at≤60 °, lost for shearing Effect；75 °≤| θ | it is tensile failure at≤90 °；
The determination of indicatrix is more complicated during classical indicatrix prediction bolt connection intensity, especially in Multi-fasteners joint When, first have to calculate the born load ratio of each nail using the method for pin load distribution, the nail to carry most serious is used as pass Keyhole, in parameter designings such as geometry, material and the layings according to crucial sky and the testpieces of test is prepared, passes through static(al) and stretches examination The extruding breaking load for obtaining perforated panel tensile failure load and stand under load hole is tested, and calculates stretching and compressive features size accordingly, Obtain indicatrix.The determination of indicatrix size needs different testpieces in different crucial hole parameter, it is costly and And expend the time.
The content of the invention
To solve the defects of prior art is present, the present invention provides a kind of more based on progressive damage model prediction composite The method for following closely connection, this method need not determine characteristic size by largely testing so that the determination of classical characteristic size More efficiently, conveniently.
The present invention technical solution be：A kind of side based on progressive damage model prediction composite Multi-fasteners joint Method, it is characterised in that including following steps：
Step 1, the model of carbon fibre composite Multi-fasteners joint is established by FEM-software ANSYS；
Step 2, pin load distribution point is carried out to carbon fibre composite Multi-fasteners joint using the FInite Element of pin load distribution Analysis, to determine the position in crucial hole；
Step 3, the breaking load of above-mentioned model is determined using APDL programmings in ANSYS；
Step 4, stretch characteristic size and compressive features size are calculated according to breaking load；
Step 5, the expression formula of classical indicatrix is determined based on resulting compression and stretch characteristic size；
The expression formula of classical indicatrix is：
rc(θ)=r0+Rt+(Rc-Rt)cosθ(-90°≤θ≤90°)
In formula, RtAnd RcRespectively stretch characteristic size and compressive features size, determined by experiment；r0For the radius in hole；θ The angle rotated clockwise or counterclockwise to drawing plane direction for the longitudinal direction extruding plane of composite connection.Attachment structure Failure mode divides according to θ position：When 0 °≤| θ | be compression failure at≤15 °；30 °≤| θ | at≤60 °, lost for shearing Effect；75 °≤| θ | it is tensile failure at≤90 °；
Step 6, the intensity and failure mode of carbon fibre composite Multi-fasteners joint are predicted according to obtained expression formula.
Further, in step 1, the implementation of carbon fibre composite Multi-fasteners joint model is：
(11), required according to required carbon fibre composite Multi-fasteners joint structural parameters, determine the laying of laminate It is required that, the geometric parameter in hole and other specification；
(12), the laying requirement based on above-mentioned laminate, the geometric parameter in hole and other parameters requirement, it is soft by finite element Part ANSYS establishes the three-dimensional finite element model of Multi-fasteners joint structure.
Further, in step 2, the analysis of carbon fibre composite Multi-fasteners joint pin load distribution determines the reality in crucial hole Now mode is：
(22) pin load distribution analysis, is carried out to carbon fibre composite Multi-fasteners joint structure using FInite Element, obtained each The load ratio that individual screw is born, wherein it is crucial hole to bear load highest, with the position in this determination key hole.
Further, the breaking load of carbon fibre composite Multi-fasteners joint model is determined using APDL programmings in ANSYS Implementation is：
(33) perforate laminate tensile failure load is obtained by the emulation of APDL command streams in ANSYS；
(34) stand under load aperture layer plywood extruding breaking load is obtained with above-mentioned same method.
Further, stretch characteristic size is calculated according to breaking load and compressive features size implementation is：
(41) after, obtaining tensile failure load, each list of perforated panel under tensile failure load is calculated using stress analysis method The stress of each point of the layer on drawing plane, brings corresponding failure criteria into, meet in each lamina point that rupture factor is 1 away from From as stretch characteristic length Rt；
(42), obtain after extruding breaking load, calculating the lower stand under load orifice plate of breaking load effect using stress analysis method squeezes Pressure failure plane on each point stress, bring corresponding failure criteria into, meet in each lamina rupture factor be 1 point away from hole side Distance be compressive features length Rc。
Further, classical indicatrix is obtained according to the stretch characteristic size obtained by the 4th step and compressive features size Implementation be：
(51), the stretch characteristic size R being calculated according to step 4t, compressive features size RcWith crucial pore radius r0；
(52), the stretch characteristic size R that will be calculatedt, compressive features size RcWith crucial pore radius r0Numerical value bring into In the expression formula of classical indicatrix, it is possible to obtain the classical indicatrix in crucial hole.
Further, the intensity and failure mode of carbon fibre composite Multi-fasteners joint are predicted according to resulting expression formula Implementation be：
(61) nail that each nail is born, is calculated and carries ratio and stress distribution；
(62), bring each stress value on indicatrix into failure criteria to be calculated, when any one on indicatrix When the rupture factor of point is more than or equal to 1, that is, think that the attachment structure fails, and then obtain carbon fibre composite Multi-fasteners joint Structural damage load.
Beneficial effect：Classics of the present invention based on progressive damage model prediction carbon fibre composite Multi-fasteners joint intensity are special Levy in curve method, the tensile failure load of laminate can be obtained by the emulation of command stream in FEM-software ANSYS and squeezed Breaking load is pressed, can thus eliminate the link of experiment so that the determination of classical characteristic size is more efficiently, conveniently； The present invention instead of conventional specimen preparation, so in carbon fibre composite Multi-fasteners joint structure by being modeled in finite element It is designed to save substantial amounts of time and cost.
Brief description of the drawings
Fig. 1 is the implementing procedure figure of the classical characteristic curve method based on experimental test；
Fig. 2 is the implementing procedure figure of the present invention；
Fig. 3 is classical characteristic curve method schematic diagram；
Fig. 4 is Multi-fasteners joint schematic diagram.
Embodiment
As shown in Figures 1 to 4, a kind of method based on progressive damage model prediction composite Multi-fasteners joint, its feature It is, including following steps：
Step 1, the model of carbon fibre composite Multi-fasteners joint is established by FEM-software ANSYS；
Step 2, pin load distribution point is carried out to carbon fibre composite Multi-fasteners joint using the FInite Element of pin load distribution Analysis, to determine the position in crucial hole；
Step 3, the breaking load of above-mentioned model is determined using APDL programmings in ANSYS；
Step 4, stretch characteristic size and compressive features size are calculated according to breaking load；
Step 5, the expression formula of classical indicatrix is determined based on resulting compression and stretch characteristic size；
The expression formula of classical indicatrix is：
rc(θ)=r0+Rt+(Rc-Rt)cosθ(-90°≤θ≤90°)
In formula, RtAnd RcRespectively stretch characteristic size and compressive features size, determined by experiment；r0For the radius in hole；θ The angle rotated clockwise or counterclockwise to drawing plane direction for the longitudinal direction extruding plane of composite connection.Attachment structure Failure mode divides according to θ position：When 0 °≤| θ | be compression failure at≤15 °；30 °≤| θ | at≤60 °, lost for shearing Effect；75 °≤| θ | it is tensile failure at≤90 °；
Step 6, the intensity and failure mode of carbon fibre composite Multi-fasteners joint are predicted according to obtained expression formula.
Further, in step 1, the implementation of carbon fibre composite Multi-fasteners joint model is：
(11), required according to required carbon fibre composite Multi-fasteners joint structural parameters, determine the laying of laminate It is required that, the geometric parameter in hole and other specification；
(12), the laying requirement based on above-mentioned laminate, the geometric parameter in hole and other parameters requirement, it is soft by finite element Part ANSYS establishes the three-dimensional finite element model of Multi-fasteners joint structure.
Further, in step 2, the analysis of carbon fibre composite Multi-fasteners joint pin load distribution determines the reality in crucial hole Now mode is：
(23) pin load distribution analysis, is carried out to carbon fibre composite Multi-fasteners joint structure using FInite Element, obtained each The load ratio that individual screw is born, wherein it is crucial hole to bear load highest, with the position in this determination key hole.
Further, the breaking load of carbon fibre composite Multi-fasteners joint model is determined using APDL programmings in ANSYS Implementation is：
(35) perforate laminate tensile failure load is obtained by the emulation of APDL command streams in ANSYS；
(36) stand under load aperture layer plywood extruding breaking load is obtained with above-mentioned same method.
Further, stretch characteristic size is calculated according to breaking load and compressive features size implementation is：
(41) after, obtaining tensile failure load, each list of perforated panel under tensile failure load is calculated using stress analysis method The stress of each point of the layer on drawing plane, brings corresponding failure criteria into, meet in each lamina point that rupture factor is 1 away from From as stretch characteristic length Rt；
(42), obtain after extruding breaking load, calculating the lower stand under load orifice plate of breaking load effect using stress analysis method squeezes Pressure failure plane on each point stress, bring corresponding failure criteria into, meet in each lamina rupture factor be 1 point away from hole side Distance be compressive features length Rc。
Further, classical indicatrix is obtained according to the stretch characteristic size obtained by the 4th step and compressive features size Implementation be：
(51), the stretch characteristic size R being calculated according to step 4t, compressive features size RcWith crucial pore radius r0；
(52), the stretch characteristic size R that will be calculatedt, compressive features size RcWith crucial pore radius r0Numerical value bring into In the expression formula of classical indicatrix, it is possible to obtain the classical indicatrix in crucial hole.
Further, the intensity and failure mode of carbon fibre composite Multi-fasteners joint are predicted according to resulting expression formula Implementation be：
(61) nail that each nail is born, is calculated and carries ratio and stress distribution；
(62), bring each stress value on indicatrix into failure criteria to be calculated, when any one on indicatrix When the rupture factor of point is more than or equal to 1, that is, think that the attachment structure fails, and then obtain carbon fibre composite Multi-fasteners joint Structural damage load.

Claims (7)

  1. A kind of 1. method based on progressive damage model prediction composite Multi-fasteners joint, it is characterised in that including following Step：
    Step 1, the model of carbon fibre composite Multi-fasteners joint is established by FEM-software ANSYS；
    Step 2, pin load distribution analysis is carried out to carbon fibre composite Multi-fasteners joint using the FInite Element of pin load distribution, with It is determined that the position in crucial hole；
    Step 3, the breaking load of above-mentioned model is determined using APDL programmings in ANSYS；
    Step 4, stretch characteristic size and compressive features size are calculated according to breaking load；
    Step 5, the expression formula of classical indicatrix is determined based on resulting compression and stretch characteristic size；
    The expression formula of classical indicatrix is：
    rc(θ)=r0+Rt+(Rc-Rt)cosθ(-90°≤θ≤90°)
    In formula, RtAnd RcRespectively stretch characteristic size and compressive features size, determined by experiment；r0For the radius in hole；θ is multiple The angle that the longitudinal direction extruding plane of condensation material connection rotates to drawing plane direction clockwise or counterclockwise.The failure of attachment structure Pattern divides according to θ position：When 0 °≤| θ | be compression failure at≤15 °；30 °≤| θ | it is shear fails at≤60 °； 75 °≤| θ | it is tensile failure at≤90 °；
    Step 6, the intensity and failure mode of carbon fibre composite Multi-fasteners joint are predicted according to obtained expression formula.
  2. 2. a kind of method based on progressive damage model prediction composite Multi-fasteners joint according to claim 1, it is special Sign is：In step 1, the implementation of carbon fibre composite Multi-fasteners joint model is：
    (11), according to required carbon fibre composite Multi-fasteners joint structural parameters requirement, determine laminate laying requirement, The geometric parameter and other specification in hole；
    (12), the laying requirement based on above-mentioned laminate, the geometric parameter in hole and other parameters requirement, pass through finite element software ANSYS establishes the three-dimensional finite element model of Multi-fasteners joint structure.
  3. 3. the method according to claim 1 based on progressive damage model prediction composite Multi-fasteners joint, its feature exist In：In step 2, the analysis of carbon fibre composite Multi-fasteners joint pin load distribution determines that the implementation in crucial hole is：
    (21) pin load distribution analysis, is carried out to carbon fibre composite Multi-fasteners joint structure using FInite Element, obtains each spiral shell The load ratio born is followed closely, wherein it is crucial hole to bear load highest, with the position in this determination key hole.
  4. 4. a kind of method based on progressive damage model prediction composite Multi-fasteners joint according to claim 1, it is special Sign is：Use the programming of APDL in ANSYS determine the breaking load implementation of carbon fibre composite Multi-fasteners joint model for：
    (31) perforate laminate tensile failure load is obtained by the emulation of APDL command streams in ANSYS；
    (32) stand under load aperture layer plywood extruding breaking load is obtained with above-mentioned same method.
  5. 5. the method according to claim 1 based on progressive damage model prediction composite Multi-fasteners joint, its feature exist In：Stretch characteristic size is calculated according to breaking load and compressive features size implementation is：
    (41) after, obtaining tensile failure load, each individual layer of perforated panel under tensile failure load is calculated using stress analysis method and existed The stress of each point on drawing plane, bring corresponding failure criteria into, meet in each lamina rupture factor be 1 point distance i.e. For stretch characteristic length Rt；
    (42), obtain after extruding breaking load, calculating the lower stand under load orifice plate extruding of breaking load effect using stress analysis method loses Imitate plane on each point stress, bring corresponding failure criteria into, meet in each lamina rupture factor be 1 point away from hole side away from From as compressive features length Rc。
  6. 6. a kind of method based on progressive damage model prediction composite Multi-fasteners joint according to claim 1, it is special Sign is：The implementation of classical indicatrix is obtained according to the stretch characteristic size obtained by the 4th step and compressive features size For：
    (51), the stretch characteristic size R being calculated according to step 4t, compressive features size RcWith crucial pore radius r0；
    (52), the stretch characteristic size R that will be calculatedt, compressive features size RcWith crucial pore radius r0Numerical value bring classics into In the expression formula of indicatrix, it is possible to obtain the classical indicatrix in crucial hole.
  7. 7. a kind of method based on progressive damage model prediction composite Multi-fasteners joint according to claim 1, it is special Sign is：According to the resulting intensity of expression formula prediction carbon fibre composite Multi-fasteners joint and the implementation of failure mode For：
    (61) nail that each nail is born, is calculated and carries ratio and stress distribution；
    (62), bring each stress value on indicatrix into failure criteria to be calculated, when any point on indicatrix When rupture factor is more than or equal to 1, that is, think that the attachment structure fails, and then obtain carbon fibre composite Multi-fasteners joint structure Breaking load.
CN201711180125.7A 2017-11-23 2017-11-23 A kind of method based on progressive damage model prediction composite Multi-fasteners joint intensity Pending CN107885946A (en)

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CN109101742A (en) * 2018-08-28 2018-12-28 南京航空航天大学 Composite material strength prediction technique based on electrical impedance imaging damage monitoring
CN109684724A (en) * 2018-12-25 2019-04-26 吉林大学 A kind of viscous compound steel skeleton construction analysis method of riveting of the more material vehicle bodies of car
CN109682680A (en) * 2018-11-29 2019-04-26 中国商用飞机有限责任公司北京民用飞机技术研究中心 A kind of complex composite material mechanical connected nail load measurement test method
CN112214848A (en) * 2020-09-18 2021-01-12 中国飞机强度研究所 Method and device for acquiring nail load of mechanical connecting piece of mixed structure
CN113722861A (en) * 2021-09-07 2021-11-30 北京航空航天大学 Method for predicting strength and failure mode of composite material bolt connection structure

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109101742A (en) * 2018-08-28 2018-12-28 南京航空航天大学 Composite material strength prediction technique based on electrical impedance imaging damage monitoring
CN109682680A (en) * 2018-11-29 2019-04-26 中国商用飞机有限责任公司北京民用飞机技术研究中心 A kind of complex composite material mechanical connected nail load measurement test method
CN109682680B (en) * 2018-11-29 2021-07-20 中国商用飞机有限责任公司北京民用飞机技术研究中心 Complex composite material mechanical connection nail load measurement test method
CN109684724A (en) * 2018-12-25 2019-04-26 吉林大学 A kind of viscous compound steel skeleton construction analysis method of riveting of the more material vehicle bodies of car
CN109684724B (en) * 2018-12-25 2020-09-15 吉林大学 Analysis method for structure of bonded and riveted composite steel skeleton of multi-material passenger car body
CN112214848A (en) * 2020-09-18 2021-01-12 中国飞机强度研究所 Method and device for acquiring nail load of mechanical connecting piece of mixed structure
CN112214848B (en) * 2020-09-18 2023-10-20 中国飞机强度研究所 Method and device for acquiring nail load of mechanical connector of hybrid structure
CN113722861A (en) * 2021-09-07 2021-11-30 北京航空航天大学 Method for predicting strength and failure mode of composite material bolt connection structure
CN113722861B (en) * 2021-09-07 2023-07-18 北京航空航天大学 Method for predicting strength and failure mode of composite material bolt connection structure

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Application publication date: 20180406