CN106156386B - A kind of slow test and predicting method for shell reinforced structure - Google Patents
A kind of slow test and predicting method for shell reinforced structure Download PDFInfo
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- CN106156386B CN106156386B CN201510169408.6A CN201510169408A CN106156386B CN 106156386 B CN106156386 B CN 106156386B CN 201510169408 A CN201510169408 A CN 201510169408A CN 106156386 B CN106156386 B CN 106156386B
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Abstract
The technology belongs to slow test and indication field, and in particular to a kind of slow test and predicting method for shell reinforced structure.By the way that structure, static(al) indicates that simulation result and test data compare under different loads effect, different boundary processing mode.On the one hand, systematicness comparison, the comprehensive assessment correlated error that slow test and static(al) indication emulate are solved, solves that control methods can only be analyzed to pole Individual features point small data in the past;On the other hand, by comparative analysis under these different stages, different boundary analog form, different solution modes, different tests method etc. are accumulated to actual experimental or simulation calculation impact factor data.In another aspect, relationship that can intuitively between reaction test and indication by comparing cloud atlas, curve, similarity, can determine whether test continues by the assessment to above-mentioned data, whether there is or not testpieces or personal safety as well as the property safety problems.
Description
Technical field
The technology belongs to slow test and indication field, and in particular to a kind of slow test for shell reinforced structure with
Predicting method.
Background technique
Carrier rocket structural strength and rigidity in development process are important examination objects, we mainly pass through 3 kinds at present
Means are analyzed: 1, Engineering Algorithm is analyzed;2, finite element indicates simulation analysis;3, entity slow test is examined.Engineering Algorithm point
Analysis is mainly used in design initial stage to structure macro strength and rigidity assessment, its main feature is that using simple, at low cost, the calculating time
Less, correct almost without visualization display, low precision, analysis result general trend, still, product this for carrier rocket,
It is required that structural units's quality high-mechanic ratio, has increasing need for designing fine structureization, Engineering Algorithm is unable to satisfy subsequent request.
It, can be with visual Simulation structure in ring and for finite element stimulation other than having the characteristics that at low cost, time is short
The variation tendency and magnitude of the numerical value such as full structural stress, strain, displacement, acceleration under the effect of border load.But since emulation is counted
During calculation, since equivalent, analysis theories the differences of the simplification of model, the constraint on boundary, material lead to simulation result
Feasibility be worth assessment.True slow test can born by the deformation of environmental load flowering structure, broken with real simulation structure
The deformation such as bad, unstability.But since following situation can be encountered in its actual mechanical process: 1, at high cost;2, measurement data has
Limit, it is impossible to pair so the point concerned measures;3, measurement space is limited, can not layout area (surface song to measurement sensor
The too large and small enclosure space of rate) it is that can not obtain measurement data;4, it in load application or boundary constraint, inevitably needs
Other auxiliary moulds, the usual rigidity of these toolings and true environment lower boundary rigidity are by part variation, and still, boundary factor is to knot
The intensity of structure, the influence of rigidity regional area is big, can not ignore;5, other environment reasons are inevitable, as temperature change, wind load become
The factor of change.
Summary of the invention
It is an object of the invention to: a kind of slow test for shell reinforced structure and predicting method are provided, they are space flight
The design and analysis of aircraft provide stronger support.
Technical scheme is as follows: a kind of slow test and predicting method for shell reinforced structure, including with
Lower step:
Step 1: establishing finite element model, establishes according to the geometric dimension of model, material, boundary condition, load corresponding
Finite element model, and analysis is calculated, obtain finite element result file;
Step 2: according to measuring point space coordinate XYZ, obtaining corresponding position finite element node serial number, to obtain measuring point letter
Breath, measuring point information are made of two files: finite element node serial number file, finite element result file,
Step 3: by measuring point space coordinate XYZ, the structure determination number of corresponding position is obtained;It is surveyed to obtain test
Point information, test measuring point information are made of two files: test structure number file, test result file,
Step 4: it is searched in the finite element model established in step 1 with test measuring point geometric position apart from nearest section
Then the freedom degree of measuring point and the freedom degree of finite element node are completed one-to-one relationship by point;
Step 5: it is set by calculating the finite element result file in step 2 with the test result file mode in step 3
Whether reliability MAC, the indication of verifying finite element and test deformation tendency are consistent, in which:
In formula, ΦeRepresent test data matrix, ΦaRepresent indication emulation FEM calculation matrix, wherein MAC value is in 0-1
In range, as MAC=0, indicates that finite element indication and test deformation tendency are entirely different, as MAC=1, indicate that the two becomes
Shape trend is identical;
Step 6: comparison diagram is drawn
Step 7: FEM updating
Test result in finite element result and step 3 in step 1 is subjected to the MAC value comparison in step 5, then
It is compared by the comparison diagram drawn in step 6, finite element model is corrected by comparison diagram version, to reach
To MAC as close possible to 1, keep calculated result and test result similarity maximum.
In the step 2, the sequence that finite element node serial number file carries out measuring point according to measuring point sequence is nX1 square
Battle array exports ess-strain displacement by finite element node serial number file, and finite element result file is by nX3 matrix description, wherein n
Measure-point amount, each column are stated by three data, and first is measuring point x coordinate, and second is y-coordinate, and third is answered for measuring point
Power, strain or displacement, for the measuring point arranged less than 3 rows or 3, if a curve, measuring point information can be plotted as under space
By 2Xn matrix description, first is classified as distance of the measuring point along curve, and second is classified as measuring point stress, strain or displacement;If cannot
It is plotted as a curve under space, then terminates.
In the step 3, the sequence that test structure number file carries out measuring point according to measuring point sequence is nX1 matrix,
Ess-strain displacement is exported by test structure number file, test result file is by nX3 matrix description, and wherein n is measuring point number
Mesh, each column are stated by three data, and first is measuring point x coordinate, and second is y-coordinate, and third is a for measuring point stress, strain
Or displacement, for less than 3 rows or 3 arrange measuring point, if a curve can be plotted as under space, test measuring point information by
2Xn matrix description, first is classified as distance of the measuring point along curve, and second is classified as measuring point stress, strain or displacement;If cannot be
It is plotted as a curve under space, then terminates.
In the step 6, when the mesh shape that can be portrayed as 3 rows, 3 column or more on measuring point direction in space, cloud is selected
Figure draws comparison diagram, wherein x coordinate is spatially transverse size;Y-coordinate is axial dimension;It is big that cloud atlas color is expressed as stress value
It is small, when there was only 1,2 rows or 1,2 column on measuring point direction in space, path correlation curve is selected to draw comparison diagram, wherein x-axis is
Path relative distance, y-axis are stress, strain or the displacement of measuring point.When comparing a certain characteristic point test data, load stage is selected
Not or load is as x-axis, and y-axis is measuring point stress, strain or displacement.
Remarkable result of the invention is: by structure in different loads effect, static(al) under different boundary processing mode
Indicate that simulation result and test data compare.On the one hand, the systematicness of solution slow test and static(al) indication emulation compares, comprehensively
Property assessment correlated error, solve in the past can only to pole Individual features point small data analyze control methods;On the other hand, pass through these
Comparative analysis under different stage, accumulation different boundary analog form, different solution modes, different tests method etc. are to actual experimental
Or simulation calculation impact factor data.In another aspect, by comparison cloud atlas, curve, similarity can intuitive reaction test with
Relationship between indication can determine whether test continues by the assessment to above-mentioned data, and whether there is or not testpieces or the person
Property safety problem.
Specific embodiment
A kind of slow test and predicting method for shell reinforced structure, includes the following steps
Step 1: establishing finite element model, establishes according to the geometric dimension of model, material, boundary condition, load corresponding
Finite element model, and analysis is calculated, obtain finite element result file;
Step 2: according to measuring point space coordinate XYZ, obtaining corresponding position finite element node serial number, to obtain measuring point letter
Breath, measuring point information are made of two files: finite element node serial number file, finite element result file, finite element node serial number text
The sequence that part carries out measuring point according to measuring point sequence, is nX1 matrix, exports ess-strain position by finite element node serial number file
It moves, finite element result file is by nX3 matrix description, and wherein n is measure-point amount, and each column are stated by three data, and first is
Measuring point x coordinate, second is y-coordinate, and third is measuring point stress, strain or displacement, for the measuring point arranged less than 3 rows or 3, if
A curve can be plotted as under space, then measuring point information is classified as distance of the measuring point along curve by 2Xn matrix description, first,
Second is classified as measuring point stress, strain or displacement;If a curve cannot be plotted as under space, terminate;
Step 3: by measuring point space coordinate XYZ, the structure determination number of corresponding position is obtained;It is surveyed to obtain test
Point information, test measuring point information are made of two files: test structure number file, test result file.Test structure number
The sequence that file carries out measuring point according to measuring point sequence, is nX1 matrix, exports ess-strain position by test structure number file
It moves, test result file is by nX3 matrix description, and wherein n is measure-point amount, and each column are stated by three data, and first is to survey
Point x coordinate, second is y-coordinate, and third is measuring point stress, strain or displacement.For the measuring point arranged less than 3 rows or 3, if can
To be plotted as a curve under space, then test measuring point information by 2Xn matrix description, first be classified as measuring point along curve away from
From second is classified as measuring point stress, strain or displacement;If a curve cannot be plotted as under space, terminate;
Step 4: it is searched in the finite element model established in step 1 with test measuring point geometric position apart from nearest section
Then the freedom degree of measuring point and the freedom degree of finite element node are completed one-to-one relationship by point;
Step 5: it is set by calculating the finite element result file in step 2 with the test result file mode in step 3
Whether reliability MAC, the indication of verifying finite element and test deformation tendency are consistent, in which:
In formula, ΦeRepresent test data matrix, ΦaRepresent indication emulation FEM calculation matrix.Wherein, MAC value is in 0-1
In range, as MAC=0, indicates that finite element indication and test deformation tendency are entirely different, as MAC=1, indicate that the two becomes
Shape trend is identical;
Step 6: comparison diagram is drawn
When the mesh shape that can be portrayed as 3 rows, 3 column or more on measuring point direction in space, cloud atlas is selected to draw comparison diagram.
Wherein, x coordinate is spatially transverse size;Y-coordinate is axial dimension;Cloud atlas color is expressed as stress value size.When measuring point space
When there was only 1,2 rows or 1,2 column on direction, path correlation curve is selected to draw comparison diagram, wherein x-axis is path relative distance,
Y-axis is stress, strain or the displacement of measuring point.When comparing a certain characteristic point test data, select load rank or load as x
Axis, y-axis are measuring point stress, strain or displacement;
Step 7: FEM updating
Test result in finite element result and step 3 in step 1 is subjected to the MAC value comparison in step 5, then
It is compared by the comparison diagram drawn in step 6, finite element model is corrected by comparison diagram version, to make
MAC value makes calculated result close to test result close to 1.
Claims (3)
1. a kind of slow test and predicting method for shell reinforced structure, it is characterised in that: the following steps are included:
Step 1: establishing finite element model, establishes according to the geometric dimension of model, material, boundary condition, load corresponding limited
Meta-model, and analysis is calculated, obtain finite element result file;
Step 2: according to measuring point space coordinate XYZ, obtaining corresponding position finite element node serial number, to obtain measuring point information, surveys
Point information is made of two files: finite element node serial number file, finite element result file,
Step 3: by measuring point space coordinate XYZ, the structure measuring point number of corresponding position is obtained;To obtain test measuring point letter
Breath, test measuring point information are made of two files: test structure number file, test result file,
Step 4: searching with test measuring point geometric position in the finite element model established in step 1 apart from nearest node,
Then the freedom degree of measuring point and the freedom degree of finite element node are completed into one-to-one relationship;
Step 5: by calculating the finite element result file in step 2 and the test result file modal assurance criterion in step 3
Whether MAC, the indication of verifying finite element and test deformation tendency are consistent, in which:
In formula, ΦeRepresent test data matrix, ΦaRepresent indication emulation FEM calculation matrix, wherein MAC value is in 0-1 range
It is interior, it as MAC=0, indicates that finite element indication and test deformation tendency are entirely different, as MAC=1, indicates that the two deformation becomes
Gesture is identical;
Step 6: comparison diagram is drawn;
When the mesh shape that can be portrayed as 3 rows, 3 column or more on measuring point direction in space, cloud atlas is selected to draw comparison diagram,
In, x coordinate is spatially transverse size;Y-coordinate is axial dimension;Cloud atlas color is expressed as stress value size, when measuring point space side
When there was only 1,2 rows or 1,2 column upwards, path correlation curve is selected to draw comparison diagram, wherein x-axis is path relative distance, y
Axis is stress, strain or the displacement of measuring point;When comparing a certain characteristic point test data, select load rank or load as x
Axis, y-axis are measuring point stress, strain or displacement;
Step 7: FEM updating
Test result in finite element result and step 3 in step 1 is subjected to the MAC value comparison in step 5, then is passed through
The comparison diagram drawn in step 6 compares, and corrects finite element model by comparison diagram version, to make MAC value
Close to 1, make calculated result close to test result.
2. a kind of slow test and predicting method for shell reinforced structure according to claim 1, it is characterised in that:
In the step 2, the sequence that finite element node serial number file carries out measuring point according to measuring point sequence is the matrix of n × 1, by having
First node serial number file output ess-strain displacement is limited, finite element result file is by the matrix description of n × 3, and wherein n is measuring point number
Mesh, every a line are stated by three data, and first is measuring point x coordinate, and second is y-coordinate, and third is measuring point stress, strains
Or displacement, for the measuring point arranged less than 3 rows or 3, if being plotted as a curve under space, measuring point information is retouched by the matrix of n × 2
It states, first is classified as distance of the measuring point along curve, and second is classified as measuring point stress, strain or displacement;If cannot be drawn under space
It is made as a curve, then is terminated.
3. a kind of slow test and predicting method for shell reinforced structure according to claim 1, it is characterised in that:
In the step 3, the sequence that test structure number file carries out measuring point according to measuring point sequence is the matrix of n × 1, passes through test
Structure number file exports ess-strain displacement, and for test result file by the matrix description of n × 3, wherein n is measure-point amount, each
Row is stated by three data, and first is measuring point x coordinate, and second is y-coordinate, and third is measuring point stress, strain or displacement,
For the measuring point arranged less than 3 rows or 3, if being plotted as a curve under space, measuring point information is tested by the matrix description of n × 2,
First is classified as distance of the measuring point along curve, and second is classified as measuring point stress, strain or displacement;If cannot be plotted as under space
One curve, then terminate.
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CN108334653B (en) * | 2017-10-20 | 2019-09-17 | 北京空天技术研究所 | A kind of Static Analysis Model of Micro-machined modification method, update the system and Static Strength Analysis method |
CN108256214B (en) * | 2018-01-16 | 2021-07-02 | 滨州学院 | Aviation orthogonal stiffened plate rigidity calculation method and device |
CN109359360B (en) * | 2018-09-30 | 2022-11-11 | 国家超级计算天津中心 | Structural stress processing method based on local features |
CN110717273B (en) * | 2019-10-11 | 2023-03-17 | 内蒙古第一机械集团股份有限公司 | Technological process simulation boundary condition construction method |
CN111639457B (en) * | 2020-06-23 | 2023-06-09 | 广州电力机车有限公司 | Design method and test method of electric wheel test fixture of mining dump truck |
CN112067265A (en) * | 2020-08-19 | 2020-12-11 | 上海航天精密机械研究所 | Testing device suitable for static force of boundary capable of sliding in one direction |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104239639A (en) * | 2014-09-18 | 2014-12-24 | 上海理工大学 | Method for simplifying parameter modification of topological optimization model of transmission shell |
CN104484526A (en) * | 2014-12-16 | 2015-04-01 | 中国第一汽车股份有限公司 | Method for improving finite element analysis accuracy of transmission case |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20020132068A1 (en) * | 2001-03-16 | 2002-09-19 | Onanov Herman George | Superstability of thin-walled structures |
-
2015
- 2015-04-10 CN CN201510169408.6A patent/CN106156386B/en active Active
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104239639A (en) * | 2014-09-18 | 2014-12-24 | 上海理工大学 | Method for simplifying parameter modification of topological optimization model of transmission shell |
CN104484526A (en) * | 2014-12-16 | 2015-04-01 | 中国第一汽车股份有限公司 | Method for improving finite element analysis accuracy of transmission case |
Non-Patent Citations (2)
Title |
---|
基于响应面方法的多目标有限元模型修正技术研究;李佰灵等;《强度与环境》;20100831;第37卷(第4期);第13-21页 * |
面向新一代运载火箭的网格加筋柱壳结构优化研究;郝鹏;《中国博士学位论文全文数据库工程科技II辑》;20140615;第1-157页 * |
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