CN114112355B - Substitution method for prefabricating pore defects of composite material structure - Google Patents
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- 230000007547 defect Effects 0.000 title claims abstract description 103
- 239000002131 composite material Substances 0.000 title claims abstract description 31
- 238000000034 method Methods 0.000 title claims abstract description 26
- 239000011148 porous material Substances 0.000 title claims abstract description 22
- 238000006467 substitution reaction Methods 0.000 title description 4
- 238000012360 testing method Methods 0.000 claims abstract description 97
- 238000004458 analytical method Methods 0.000 claims abstract description 74
- 230000006378 damage Effects 0.000 claims abstract description 42
- 238000012795 verification Methods 0.000 claims abstract description 24
- 239000000463 material Substances 0.000 claims abstract description 19
- 230000032798 delamination Effects 0.000 claims abstract description 13
- 238000009417 prefabrication Methods 0.000 claims abstract description 10
- 238000004088 simulation Methods 0.000 claims abstract description 6
- 238000012216 screening Methods 0.000 claims abstract description 5
- 238000010521 absorption reaction Methods 0.000 claims description 12
- 239000011800 void material Substances 0.000 claims description 9
- 238000004364 calculation method Methods 0.000 claims description 7
- 230000003068 static effect Effects 0.000 claims description 4
- 230000000007 visual effect Effects 0.000 claims description 4
- 238000012937 correction Methods 0.000 claims description 3
- 238000013461 design Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 230000035882 stress Effects 0.000 description 7
- 230000032683 aging Effects 0.000 description 2
- 230000002950 deficient Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 201000003874 Common Variable Immunodeficiency Diseases 0.000 description 1
- 230000003679 aging effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000013590 bulk material Substances 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000008961 swelling Effects 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/0202—Control of the test
- G01N2203/0212—Theories, calculations
- G01N2203/0216—Finite elements
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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
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Abstract
The invention provides an alternative method for prefabricating pore defects of a composite material structure, which comprises the following steps: determining a porosity sample, an impact damage sample and a delamination defect sample; determining the mechanical property of the material structure of the porosity sample based on the porosity to obtain a first analysis result; determining the mechanical properties of the impact damage sample and the layering defect sample based on the impact damage and the layering defect to obtain a second analysis result; performing accurate finite element test simulation analysis to obtain a finite element analysis result; screening out that the mechanical properties of layering or layering and impact defects are close to those of pore defects based on the first analysis result and the second analysis result; and selecting layering defects or layering and impact damage defects capable of replacing porosity based on the finite element analysis result and combining the first analysis result and the second analysis result, performing defect prefabrication on the part structure, and finishing part test verification.
Description
Technical Field
The invention relates to the technical field of aviation science, in particular to a replacement method for prefabricating pore defects of a composite material structure.
Background
The composite material has the advantages of light weight, good fatigue resistance, corrosion resistance, convenience for large-area integral molding, high specific strength/specific stiffness and the like, and is increasingly widely applied in the aerospace field. In order to ensure that the composite material has the same high safety level as the metal structure, a large amount of funds are invested in European and American countries to carry out verification research on the composite material structure, the starting is earlier, and a large amount of experience and data are accumulated.
The composite material structure is relatively late in application in the aviation field of China, and particularly in the application of a bearing structure. The composite material structure verification relates to a plurality of fields such as static strength analysis, fatigue analysis, damage tolerance analysis and the like, the composite material structure in the early aviation field is in a test verification mode according to a metal structure, defects are not considered to be inherent properties of the composite material structure, and test verification is not carried out on prefabricated defects of a test piece in the test verification. The pores are common defects of the composite material structure, when the porosity is smaller, the influence on the mechanical property of the structure is relatively smaller, and when the porosity is increased, the pores can become crack initiation points, particularly when the long axis direction of the pores is perpendicular to the load direction, the higher porosity can cause the coupling association of cracks initiated in adjacent different pores, so that the mechanical property of the structure is obviously influenced; the porosity of the laminate deteriorates the moisture absorption properties of the composite material, and when moisture in the environment accumulates in the matrix to cause the pore region to fill with water, and thereafter, the composite material is exposed to a high temperature environment, swelling and aging of the composite material are accelerated by the evaporation of the water, and further microcracks may be generated in the matrix due to the steam pressure, thereby aggravating the moisture absorption and aging properties of the material.
Therefore, in the air-fit evidence-obtaining verification of the composite material part structure of the civil aircraft, the influence of the pore on the structure must be considered, but because the pore defects can not be quantitatively prefabricated like defects of layering, debonding, impact damage and the like, in the verification process of the composite material part structure, the domestic basic practice is that the test verification is carried out without considering the influence of the pore defects or prefabricating related pore defects when the test verification of the composite material part structure is carried out, so that the composite material structure is not fully verified, and the reliability and the safety of the composite material structure cannot be well ensured.
Disclosure of Invention
In view of the above technical problems, the present invention provides an alternative method for prefabricating void defects in a composite structure, the method comprising:
determining a sample; wherein the sample comprises a porosity sample, an impact damage sample and a layering defect sample;
determining the mechanical property of the material structure of the porosity sample based on the porosity to obtain a first analysis result;
determining the mechanical properties of the impact damage sample and the layering defect sample based on the impact damage and the layering defect to obtain a second analysis result;
performing accurate finite element test simulation analysis to obtain a finite element analysis result;
screening out that the mechanical properties of layering or layering and impact defects are close to those of pore defects based on the first analysis result and the second analysis result;
and selecting layering defects or layering and impact damage defects capable of replacing porosity based on the finite element analysis result and combining the first analysis result and the second analysis result, performing defect prefabrication on the part structure, and finishing part test verification.
Preferably, the determining the sample includes:
and manufacturing a test piece for testing the component assembly combined with the composite material building block type verification requirement, and determining a porosity sample piece based on the test result of the test piece and the porosity meeting the acceptance requirement.
Preferably, the determining the sample further includes:
and prefabricating layering defects on the sample pieces, prefabricating sample pieces with different layering sizes, and obtaining layering defect sample pieces.
Preferably, the determining the mechanical property of the material structure of the porosity sample based on the porosity, to obtain the first analysis result, includes:
selecting a porosity sample with larger porosity and close to a critical value within the porosity range allowed by acceptance;
carrying out a mechanical property test of the porosity sample piece under normal temperature conditions;
performing a mechanical property test of the porosity sample after moisture absorption and balance;
and comparing and analyzing the test result with the component-level conventional part to obtain a first analysis result.
Preferably, the determining the mechanical properties of the impact damage sample and the delamination defect sample based on the impact damage and the delamination defect, to obtain a second analysis result, includes:
one third of layered defect sample pieces are overlapped and can be barely detected by visual sense, and one third of layered defect sample pieces are overlapped and can be obviously detected by visual sense to impact damage;
performing a mechanical property test of the layering defect sample piece at normal temperature;
performing a mechanical property test of the layered defect sample after moisture absorption and balance;
and comparing and analyzing the test result with the component-level conventional part to obtain a second analysis result.
Preferably, the performing accurate finite element test simulation analysis to obtain finite element analysis results includes:
carrying out stress analysis on a sample piece which is not subjected to defect prefabrication and impact damage through a finite element calculation result, defining the structure size of the machine body which meets the design requirement of static strength, carrying out modeling analysis on the structure which is subjected to the test through the finite element modeling method, comparing the structure with the test result, and correcting modeling details;
and carrying out stress influence analysis on the test piece of the component with the defect according to a finite element analysis method for correcting modeling details, carrying out a test, carrying out comparison analysis on the test piece and the test result, correcting the finite element modeling method of the part with the defect, and carrying out stress calculation analysis on the structural component with the prefabricated defect and the impact damage according to a modeling method for secondary correction to obtain a finite element analysis result.
Preferably, the determining the mechanical property of the material structure of the porosity sample based on the porosity, to obtain the first analysis result, further includes:
and determining the mechanical property of the material structure of the porosity sample piece based on the porosity through a component level test, and obtaining a first analysis result.
Preferably, the determining the mechanical properties of the impact damage sample and the delamination defect sample based on the impact damage and the delamination defect, to obtain a second analysis result, further includes:
and determining the mechanical properties of the impact damage sample and the layering defect sample based on the impact damage and the layering defect through a component level test, and obtaining a second analysis result.
The beneficial technical effects of the invention are as follows:
the invention solves the technical bottleneck of verification that the void defects cannot be considered in the verification of the composite material structure of the aircraft, breaks through the traditional thought that the test piece is not prefabricated and the void defects are not considered in the verification, forms the substitution method of prefabrication of the void defects of the composite material structure part of the aircraft, fully verifies the composite material structure part, and further improves the flight safety level of the aircraft.
Drawings
FIG. 1 is a schematic view of an apertured tensile test member;
FIG. 2 is a schematic diagram of strain measurement;
FIG. 3 is a tail section finite element model;
FIG. 4 is a schematic diagram of void defects;
FIG. 5 is a schematic representation of impact damage + delamination (debonding) instead of void defects;
FIG. 6 is a partial detail view of an impact damage substitution defect;
fig. 7 is a partial detail view of an impact + delamination replacement void defect.
Detailed Description
Referring to fig. 1-7, it is an object of the present invention to provide an alternative method for prefabrication of porosity defects, which simulates the defects of a substitute porosity for verification by one or a combination of several other defects during verification of the structure of a composite part.
The invention can be popularized to the verification of composite material structures in other industries outside the field of aircrafts, and has positive significance in improving the safety level.
Screening out a part of samples with porosity close to porosity determined by a given acceptance requirement during test verification of a material grade; preliminarily determining the influence of porosity on mechanical properties through a component level test; according to the acceptable structural layering defects determined by the acceptance requirements, prefabricating layering defect test pieces with different degrees of inspection capability within the range of the layering defect test pieces; on a part of layering defect test piece, prefabricating impact damage defects, and determining the influence (combination environment) of the defects such as impact, layering and the like on the mechanical properties of materials through a component level test; analysis of the combined test results determines which defect or combination of defects can simulate the void defect relatively closely; during the test, other defects are used for simulating and replacing pore defects to carry out test verification, and the specific steps are as follows:
step one:
1. manufacturing a test piece for testing the component assembly combined with the composite material building block type verification requirement, and selecting a sample piece with the porosity close to the porosity determined by the established acceptance requirement according to the test result of the test piece;
2. the porosity herein refers to the bulk porosity, which refers to the percentage of the pore volume in the bulk material to the total volume of the material in its natural state, and is generally calculated as the relationship between formula and density:
p-porosity (%) of material;
V 0 the volume of the material in its natural state, or apparent volume (cm) 3 Or m 3 )；
V-absolute compact volume of material (cm) 3 Or m 3 )；
ρ 0 Material apparent Density (g/cm) 3 Or kg/m 3 )；
ρ -Material Density (g/cm) 3 Or kg/m 3 )
Step two: the influence of porosity on the mechanical properties of materials and structures is preliminarily determined through a test of a component level, and the method comprises the following substeps:
1. selecting a typical sample with larger porosity and close to a critical value within the range of porosity allowed by acceptance;
2. carrying out mechanical property test on each typical sample at normal temperature;
3. performing a mechanical property test of each typical sample after moisture absorption and balance;
4. and comparing and analyzing the test results with the test results of the conventional component of the component level.
Step three: through a test of a component level, the influence of impact damage and layering on mechanical properties is preliminarily determined, and the steps are as follows:
1. according to the acceptable structural layering defects determined by the acceptance requirements, prefabricating typical test samples with different layering sizes and different degrees of inspection capability within the range;
2. one third of the samples were superimposed with barely visually detectable (BVID) and one third of the samples were superimposed with visibly apparent detectable (CVID) impact damage;
3. carrying out mechanical property test on each typical sample at normal temperature;
4. performing a mechanical property test of each typical sample after moisture absorption and balance;
5. and comparing and analyzing the test results with the test results of the conventional component level.
Step four: performing an accurate finite element test simulation analysis, comprising the sub-steps of:
1. performing stress analysis on the parts which are not subjected to defect prefabrication and impact damage through an MSC. Nastran finite element calculation result, defining the structure size of the machine body which meets the design requirement of static strength, performing modeling analysis on the structure which is subjected to the test through the finite element modeling method, comparing the modeling analysis with the test result, and correcting modeling details;
2. and carrying out stress influence analysis on the test piece with the defective component level according to a finite element analysis method for correcting modeling details, then carrying out a test, comparing and analyzing with test results, correcting the finite element modeling method of the defective part, and carrying out stress calculation analysis on the structural component with the prefabricated defect and impact damage according to a modeling method for secondary correction.
Step five: and (3) comparing the influence of the defects in the second step and the third step on the mechanical properties, and screening out the mechanical properties of the layering defects or the layering and impact damage defects, wherein the mechanical properties are close to those of the pore defects.
Step six: and selecting layering defects or layering and impact damage defects which can replace porosity according to the finite element analysis result and the element assembly test condition, and performing defect prefabrication on the part structure to finish the part test verification.
The technical scheme of the invention is further described below with reference to specific embodiments.
Example 1:
step two and step three:
taking a composite tail beam of a certain machine as an example:
the mechanical property test of the normal component and the typical component in the second step and the third step mainly comprises the test items in the following table, and the larger the number of the test components is theoretically, the smaller the dispersity of the result is.
Component mechanical property test item and method
Wet test piece state adjustment to ensure that the sample piece has reached moisture absorption equilibrium state
The test piece was put into a CP111751 wet heat test box, the ambient temperature was set to 70 ℃ and 85% relative humidity, a wet heat aging test was performed on the test piece, the test piece was weighed every 24 hours, and the weight change of the test piece was recorded. Until the weight change Wm (calculated by the formula (1)) of the standard moisture absorption test piece is less than 0.02% in 24 hours, the test piece reaches the moisture absorption balance, and the state adjustment is stopped.
(1) Wherein:
W i -the sample mass measured for the i-th time in grams (g);
W i-1 -the mass of the sample measured in grams (g) for the i-1 st time;
W od -the engineering dry state quality of the product,the unit is gram (g);
W m changes in weight of the sample when equilibrium of moisture absorption is reached.
After the wet sample condition is adjusted, the sample can be taken out of the infiltration box and placed into a sealed bag together with a wet tissue until the mechanical test is performed, wherein the storage time of the sample in the sealed bag should not exceed 14 days.
Tensile Strength of open pore
The open cell tensile strength is calculated according to formula (1).
(2) Wherein:
open cell tensile strength, MPa;
P max -maximum load before failure, N;
a-wool cross-sectional area (ignoring holes), mm, obtained from the product of sample width and thickness 2 。
Step four: finite element modeling is carried out, stress calculation analysis is carried out, and the finite element model is specifically shown in fig. 3.
Step five: experiments prove that the impact damage and delamination (debonding) between the frames of the left wall panels W7-W8 are used for replacing the pore defects, and the impact damage and delamination (debonding) between the frames of the left wall panels W7-W8 are used for replacing the pore defects, as shown in figures 4 and 5. The detail view is shown in fig. 6 and 7.
Claims (5)
1. An alternative method of void defect prefabrication of a composite structure, the method comprising:
determining a sample; wherein the samples include a porosity sample, an impact damage sample, and a delamination defect sample, the impact damage sample being prefabricated on the basis of the delamination defect sample;
determining the mechanical property of the material structure of the porosity sample based on the porosity to obtain a first analysis result;
determining the mechanical properties of the impact damage sample and the layering defect sample based on the impact damage and the layering defect to obtain a second analysis result;
performing accurate finite element test simulation analysis to obtain a finite element analysis result;
screening out that the mechanical properties of layering or layering and impact defects are close to those of pore defects based on the first analysis result and the second analysis result;
selecting layering defects or layering and impact damage defects capable of replacing porosity based on the finite element analysis result and combining the first analysis result and the second analysis result, performing defect prefabrication on a part structure, and finishing part test verification;
wherein, the determining the mechanical property of the material structure of the porosity sample based on the porosity, to obtain a first analysis result, includes:
selecting a porosity sample with larger porosity and close to a critical value within the porosity range allowed by acceptance;
carrying out a mechanical property test of the porosity sample piece under normal temperature conditions;
performing a mechanical property test of the porosity sample after moisture absorption and balance;
comparing and analyzing the test result with the conventional component of the component level to obtain a first analysis result;
the determining the mechanical properties of the impact damage sample and the layering defect sample based on the impact damage and the layering defect to obtain a second analysis result comprises the following steps:
one third of layered defect sample pieces are overlapped and can be barely detected by visual sense, and one third of layered defect sample pieces are overlapped and can be obviously detected by visual sense to impact damage;
performing a mechanical property test of the layering defect sample piece at normal temperature;
performing a mechanical property test of the layered defect sample after moisture absorption and balance;
comparing and analyzing the test result with the conventional component of the component level to obtain a second analysis result;
the step of performing accurate finite element test simulation analysis to obtain a finite element analysis result comprises the following steps:
carrying out stress analysis on a sample piece which is not subjected to defect prefabrication and impact damage through a finite element calculation result, defining the structure size of the machine body which meets the design requirement of static strength, carrying out modeling analysis on the structure which is subjected to the test through the finite element modeling method, comparing the structure with the test result, and correcting modeling details;
and carrying out stress influence analysis on the test piece of the component with the defect according to a finite element analysis method for correcting modeling details, carrying out a test, carrying out comparison analysis on the test piece and the test result, correcting the finite element modeling method of the part with the defect, and carrying out stress calculation analysis on the structural component with the prefabricated defect and the impact damage according to a modeling method for secondary correction to obtain a finite element analysis result.
2. The method of claim 1, wherein the determining the sample comprises:
and manufacturing a test piece for testing the component assembly combined with the composite material building block type verification requirement, and determining a porosity sample piece based on the test result of the test piece and the porosity meeting the acceptance requirement.
3. The method of claim 1, wherein the determining the sample further comprises:
and prefabricating layering defects on the sample pieces, prefabricating sample pieces with different layering sizes, and obtaining layering defect sample pieces.
4. The method of claim 1, wherein determining the mechanical properties of the material structure of the porosity sample based on the porosity yields a first analysis result, further comprising:
and determining the mechanical property of the material structure of the porosity sample piece based on the porosity through a component level test, and obtaining a first analysis result.
5. The method of claim 1, wherein determining mechanical properties of the impact damaged and delamination defect samples based on the impact damaged and delamination defect samples, results in a second analysis result, further comprises:
and determining the mechanical properties of the impact damage sample and the layering defect sample based on the impact damage and the layering defect through a component level test, and obtaining a second analysis result.
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