CN109684693A - A method of based on the estimated Material Stiffened Panel post-buckling of finite element analysis - Google Patents
A method of based on the estimated Material Stiffened Panel post-buckling of finite element analysis Download PDFInfo
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- CN109684693A CN109684693A CN201811518720.1A CN201811518720A CN109684693A CN 109684693 A CN109684693 A CN 109684693A CN 201811518720 A CN201811518720 A CN 201811518720A CN 109684693 A CN109684693 A CN 109684693A
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- 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]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The present invention relates to the methods based on the estimated Material Stiffened Panel post-buckling of finite element analysis, first carry out simulation modeling to Material Stiffened Panel shearing test part, carry out Linear buckling analysis, obtain Material Stiffened Panel shear performance value buckling mode；Before carrying out nonlinear buckling analysis, Material Stiffened Panel single order buckling mode vector is normalized, defect offset vector is obtained multiplied by defect base vector, apply forced modal displacement by SPCD model data card, the defect in area will be examined to be introduced into the form of updating unit node coordinate and improved in Material Stiffened Panel structure；Consider the big degree of disturbing and plastic effect of Material Stiffened Panel post-buckling, post-buckling calculating is carried out to structure, apply point from load-displacement curve prediction Material Stiffened Panel bearing capacity of the stress deformation to structure post-buckling destructive process is started by load, the accuracy and engineering feasibility of this method are demonstrated by test result；With method of the invention, physical test is reduced, it is significant to reduction experimentation cost and risk.
Description
Technical field
The invention belongs to aeronautic structure design fields, and in particular to one kind is based in the wrong after the estimated Material Stiffened Panel of finite element analysis
Bent method.
Background technique
Material Stiffened Panel is the important bearing structure of aircraft, hits, under aircarrier aircraft landing configuration, covers in ship-board aircraft warship
The case where shear stress that skin is born be will appear greater than critical shear stress, covering starts unstability at this time, due to depositing for siding reinforcing rib
It can also continue to bear increased external applied load after covering unstability, but its internal force is redistributed, unstability ripple number increases simultaneously therewith
Tend to rule, can finally occur to shear post-buckling destruction.In aircraft big overload flight, Material Stiffened Panel axial compression load is often
Peak value can be reached, buckling, which can occur, for siding even destroys.At present in engineering to the calculating of the Buckling of Material Stiffened Panel still first
Buckling stage beginning, and need to consider that the engineering post-buckling calculation method of big degree of disturbing and plastic effect is also immature.Existing aircraft is set
Calculate in meter about Material Stiffened Panel post-buckling be always design field problem, the post-buckling of the Material Stiffened Panel material that interweaved is non-thread
Property and geometrical non-linearity, classical elastic stability theory not can solve.Half theory half that the theory of follow-up developments and test combine
Test method may measure in advance bearing capacity partially although application is convenient in engineering due to ignoring certain failure modes
Height, or measured bearing capacity in advance relatively low since buckling is considered as destruction.
Summary of the invention
The purpose of the present invention is: a kind of method based on the estimated Material Stiffened Panel post-buckling of finite element analysis is designed, to solve
At present present in physical test it is at high cost, the time is long, risk is big and engineering calculating method in precision is not high causes structure efficiency
Relatively low technical problem.
To solve this technical problem, the technical scheme is that
A method of it is described to expect to add based on finite element analysis based on the estimated Material Stiffened Panel post-buckling of finite element analysis
The method of muscle siding post-buckling mainly comprises the steps that
1, simulation modeling is carried out to Material Stiffened Panel shearing test part based on finite element analysis software；
2, linear buckling solution is carried out with finite element analysis software solver；
3, it using consistent mode imperfection method, programs, the linear buckling result of area's displacement field will be examined to draw as disturbance
Enter model；
4, bond material/geometry Double Nonlinear simulates its big degree of disturbing and plastic effect, calls nonlinear solver, uses
Arc-length methods carry out post-buckling calculating to structure, obtain calculated result file；
5, it extracts load and is displaced and calculate as a result, obtaining load applies point from stress deformation is started to the destruction of structure post-buckling
Post-buckling ultimate bearing capacity can be obtained in the load-displacement curves of process.
In the step 1 when carrying out simulation modeling to Material Stiffened Panel specifically: under shear load, each half-wave is extremely
5 nodes are chosen less；Under compressive loading, each half-wave at least chooses 3 nodes.
Single order instability modes are at least solved in the step 2 when linear buckling solves.
The step 3 specifically:
1) it programs manually, extracts the displacement field in single order instability modes examination area；
2) apply displacement field in the form of data card as initial imperfection, explicit presentation initial imperfection form；
The step 4 specifically:
1) added material Non-linear constitutive model, the input of nonlinear stress and strain data；
2) consider large deformation, call nonlinear solver to carry out post-buckling calculating to structure, obtain calculated result file.
The step 5 specifically:
1) destination file is imported into finite element analysis software, draws the load-displacement curves of load(ing) point, obtain limit load
Lotus；
2) calculated result for extracting load and displacement draws examination area's key position load-strain curve, obtains limit load
Lotus and destructive process.
The solution have the advantages that:
The present invention is based on finite element softwares to calculate Material Stiffened Panel post-buckling bearing capacity using consistent mode defect method.
1. giving the step of predicting bearing capacity using finite element software and method；
2. explicit to present by initial disturbance form by forcing shifted version to apply；
3. giving the method by the estimated bearing capacity of software, physical test cost is greatly saved.
Method of the method for the present invention based on the estimated Material Stiffened Panel post-buckling of finite element software, is designed in aircraft wing skins
In, pre-stage test data are based on, using virtual test, reduce physical test, design efficiency is improved, the reduction design cycle, reduces
Experimentation cost is significant.
Detailed description of the invention
Method flow schematic diagram Fig. 1 of the invention；
The specific flow chart of the embodiment of Fig. 2 the method for the present invention；
The testpieces front view of Fig. 3 the method for the present invention
The testpieces sectional view of the embodiment of Fig. 4 the method for the present invention；
Fig. 5 7150-T7751 plate stress-strain curves；
Fig. 6 Material Stiffened Panel loading end load-displacement curve figure；
Wherein, 1 is examination area, and 2 be transition region.
Specific embodiment
Method of the invention is described in detail with reference to the accompanying drawings of the specification:
The method of the present invention flow diagram by taking specific embodiment as an example as shown in Figure 1, be described in detail as follows below: example
Middle testpieces front view is as shown in Figure 3, wherein 1 is examination area, and 2 be transition region, and concrete specification is as follows:
The examination section length of Material Stiffened Panel shearing test part is 700mm, and the examination area of testpieces is by 4 identical stringer lists
Member composition, stringer unit section are as shown in Figure 4.Examination area's surrounding stretches out transition region for being connected with test fixture, and transition region is thick
Degree is 10.5mm, width 150mm.
Specific sectional parameter is shown in Table 1.
The sectional parameter of 1 testpieces of table
Wherein, t is stringer web thickness, and t1 and b are respectively the thickness and width of the free flange of stringer, and t2 and b1 are respectively
The thickness and width of stringer bottom edge flange, h are stringer height, and R and R1 are chamfering radius.
2 it is shown specific flow chart with reference to the accompanying drawings, circular is as follows:
1, simulation modeling is carried out to Material Stiffened Panel shearing test part based on finite element analysis software；
When finite element modeling, the simulation of covering and stringer considers integral reinforced siding, stringer and illiteracy using four node shell members
Skin conode.In order to preferably simulate the local buckling of covering, using the finite element model of refinement.Compared with compressing flexural wave,
The wavelength of shear buckling wave is smaller, therefore needs finite element grid fine and closely woven enough under shear load to simulate shearing instability wave,
Every half-wave at least uses 5 nodes.
2, linear buckling solution is carried out with finite element analysis software solver；
Linear buckling analysis obtains the critical mistake of structure by extracting the characteristic value for keeping linear system stiffness matrix unusual
Steady load and instability modes.MSC.Nastran software SOL105 is that Linear buckling analysis solves sequence, and being suitable for structure is small change
Shape, element stress must be solved in ranges such as elastic (stress-strain relation are linear), therefore nonlinear material is become with big
Shape structure, the linear buckling load and actual critical load difference that SOL105 is calculated are larger.It is linearly bent by SOL105
Bent Eigenvalues analysis obtains Material Stiffened Panel shear performance value buckling mode.
3, it using consistent mode imperfection method, programs, the linear buckling result of area's displacement field will be examined to draw as disturbance
Enter model；
Before carrying out nonlinear buckling analysis, Material Stiffened Panel single order buckling mode vector is normalized, multiplied by defect base vector
10-3 obtains defect offset vector, applies forced modal displacement by SPCD model data card, with updating unit node coordinate
Form the defect in area will be examined to be introduced into improve in Material Stiffened Panel structure.
4, bond material/geometry Double Nonlinear simulates its big degree of disturbing and plastic effect, calls nonlinear solver, uses
Arc-length methods carry out post-buckling calculating to structure, obtain calculated result file；
In MSC.Patran definition material elastic-plastic constitutive relation, first input flexibility deformation parameter, the sheet of definition material
Structure is elastic model；The constitutive model of the material is appointed as elastoplasticity again, nonlinear stress and strain data are called by Field
The coordinate inputted point by point in Fig. 5 completes the addition of Non-linear constitutive model.
By the nonlinear buckling analysis of increment definition, it can consider that material and geometrical non-linearity is steady to structure simultaneously simultaneously
It qualitatively influences, after choosing material constitutive relation, activates options, the programs such as LGDISP that can automatically exist in step increment method analysis
Contribution of the material nonlinearity to stiffness matrix is calculated on the basis of geometrical non-linearity.
It calls MARC nonlinear solver to carry out post-buckling calculating to structure, obtains calculated result file (*
.marc.t16)。
5, it extracts load and displacement calculates as a result, using arc-length methods to structure progress post-buckling calculating, obtain load application
Post-buckling ultimate bearing energy can be obtained from stress deformation is started to the load-displacement curves of structure post-buckling destructive process in point
Power.
Destination file * .marc.t16 is imported into MSC.Patran, extracts the calculated result of load and displacement, draws load-
Displacement curve is as shown in Figure 6.The extreme point of curve is post-buckling ultimate bearing capacity.
The comparative analysis of test result and finite element predictions is described below, demonstrates the correct of Finite element analysis results
Property and feasibility.Play booster action.
3 Material Stiffened Panel shearing test parts of parameter are tested in table 1, the test of buckling load and finite element result
Compare and be shown in Table 2, the test of breaking load is shown in Table 3 compared with finite element result, while giving test load average value.
The test of 2 buckling load of table is compared with finite element result
The test of 3 breaking load of table is compared with finite element result
First in table corresponds to testpieces number, PTESTFor testpieces load, i.e. test value, PFEAFor FEM calculation value, ε
Error for FEM calculation value relative to test value:
ε=(PTEST-PFEA)/PTEST× 100%
As it can be seen that using the initial buckling load and breaking load of the Material Stiffened Panel shearing post-buckling of FEM calculation and test
It is worth error within 5%, initial buckling load and the test load average value error that finite element stimulation obtains are
1.25%, breaking load average value error is 2.4%.Siding examines the strain on district center point with the meter of load step change curve
The comparison of calculation value and test value is as shown in Figure 6.
Claims (6)
1. a kind of method based on the estimated Material Stiffened Panel post-buckling of finite element analysis, it is characterised in that: described based on finite element
The method for analyzing estimated Material Stiffened Panel post-buckling mainly comprises the steps that
1.1, simulation modeling is carried out to Material Stiffened Panel shearing test part based on finite element analysis software；
1.2, linear buckling solution is carried out with finite element analysis software solver；
1.3, it using consistent mode imperfection method, programs, the linear buckling result of area's displacement field will be examined to introduce as disturbance
Model；
1.4, bond material/geometry Double Nonlinear simulates its big degree of disturbing and plastic effect, nonlinear solver is called, using arc
Regular way carries out post-buckling calculating to structure, obtains calculated result file；
1.5, extraction load and displacement are calculated and were destroyed as a result, obtaining load and applying point from beginning stress deformation to structure post-buckling
Post-buckling ultimate bearing capacity can be obtained in the load-displacement curves of journey.
2. the method according to claim 1 based on the estimated Material Stiffened Panel post-buckling of finite element analysis, it is characterised in that: institute
In the step 1.1 stated when carrying out simulation modeling to Material Stiffened Panel specifically: under shear load, each half-wave at least chooses 5
A node；Under compressive loading, each half-wave at least chooses 3 nodes.
3. the method according to claim 1 based on the estimated Material Stiffened Panel post-buckling of finite element analysis, it is characterised in that: institute
Single order instability modes are at least solved in the step 1.2 stated when linear buckling solves.
4. the method according to claim 1 based on the estimated Material Stiffened Panel post-buckling of finite element analysis, it is characterised in that: institute
The step 1.3 stated specifically:
4.1, it programs manually, extracts the displacement field in single order instability modes examination area；
4.2, apply displacement field in the form of data card as initial imperfection, explicit presentation initial imperfection form.
5. the method according to claim 1 based on the estimated Material Stiffened Panel post-buckling of finite element analysis, it is characterised in that: institute
The step 1.4 stated specifically:
5.1, added material Non-linear constitutive model；
5.2, consider large deformation, call nonlinear solver to carry out post-buckling calculating to structure, obtain calculated result file.
6. the method according to claim 1 based on the estimated Material Stiffened Panel post-buckling of finite element analysis, it is characterised in that: institute
The step 1.5 stated specifically:
6.1, destination file is imported into finite element analysis software, draws the load-displacement curves of load(ing) point, obtains ultimate load；
6.2, the calculated result of load and displacement is extracted, examination area's key position load-strain curve is drawn, obtains ultimate load
And destructive process.
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| CN110096808A (en) * | 2019-04-30 | 2019-08-06 | 中国石油工程建设有限公司北京设计分公司 | A kind of spherical shell vault Finite Element Simulation Analysis method with ribbing under multiple spot load |
| CN110119560A (en) * | 2019-04-30 | 2019-08-13 | 中国空间技术研究院 | A method of telecommunication satellite flexible waveguide intensity is checked based on radius of curvature |
| CN110702525A (en) * | 2019-08-05 | 2020-01-17 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Ultra-large floating body ultimate strength testing device and testing method under bending load |
| CN110737997A (en) * | 2019-08-05 | 2020-01-31 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Method for analyzing ultimate strength of ultra-large floating body structure under complex load effect |
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| CN112763320A (en) * | 2020-12-29 | 2021-05-07 | 中国航空工业集团公司西安飞机设计研究所 | Method for judging buckling load when shaft pressure load is borne by body wallboard |
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