CN111143941A - Method for calculating axial compression bearing capacity of composite material reinforced wall plate - Google Patents
Method for calculating axial compression bearing capacity of composite material reinforced wall plate Download PDFInfo
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- CN111143941A CN111143941A CN201911346533.4A CN201911346533A CN111143941A CN 111143941 A CN111143941 A CN 111143941A CN 201911346533 A CN201911346533 A CN 201911346533A CN 111143941 A CN111143941 A CN 111143941A
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Abstract
The invention discloses a method for calculating the axial pressure bearing capacity of a composite material reinforced wall plate, which considers the factors that the modulus of a skin is possibly different from that of a stringer, then calculates the axial pressure damage load by considering the section of a stiffened plate of the skin with the effective width, and then superposes the bearing capacity of a locally bent skin to finally obtain the bearing capacity of the whole stiffened plate.
Description
Technical Field
The invention belongs to the technical field of aviation strength, and particularly relates to a method for calculating the axial compression bearing capacity of a composite material reinforced wall plate.
Background
In order to reduce weight and fully excavate the bearing capacity of the structure, the thin-wall reinforced structure is a form often adopted in the design of an airplane. Because the specific modulus and the specific strength are high, the composite material has great advantages in weight reduction, and the composite material is more and more widely used for airplane structures, so that the composite material reinforced wall plate is a preferred scheme in airplane structure design.
The axial compression is a main loading form of the composite material reinforced wall plate, and how to accurately estimate the axial pressure bearing capacity of the composite material reinforced wall plate is an important basis for ensuring the flight safety of an airplane and the weight reduction design of a structure and is also an important problem to be solved by current engineering designers. The existing engineering calculation method is compared with test results to find that some results have larger errors and some results are more dangerous than the test values, and a numerical solving method based on a finite element theory is too complicated, and more adjustable parameters are used in calculation, so that the uncertainty of the results is increased, and the method is not suitable for engineering application. In summary, no widely accepted calculation method for the composite material reinforced wall plate exists in the engineering industry at present, and the method is suitable for estimating the axial pressure bearing capacity of the composite material reinforced wall plate.
Disclosure of Invention
The purpose of the invention is as follows: the method for calculating the axial compression bearing capacity of the composite material reinforced wall plate can reduce the error of a calculation result, can ensure that the error is lower than a test value, and is suitable for engineering application. .
The technical scheme of the invention is as follows:
a method for calculating the axial compression bearing capacity of a composite material reinforced wall plate comprises the following steps:
step 1: giving the average failure stress sigma of the stiffened panel to be calculatedcoAssigning an initial value;
step 2: calculating the effective width b of the skine；
And step 3: calculating the gyration radius and rho and equivalent modulus of the stringer and effective width skin combined section
And 4, step 4: calculating mean failure stress σ 'of stringer and effective width skin composite section'co；
And 5: judging sigma'coAnd σcoWhether or not | σ is satisfiedco-σ′coEpsilon is less than or equal to | is less than or equal to; if so, then σcoAs the average failure stress of the stiffened plate, if not, the stress is sigma'coAssigned to σcoThen, steps 2 to 5 are repeated until | σ is satisfiedco-σ′coI.ltoreq.epsilon, where epsilon is setThe threshold value of (2) for controlling the calculation accuracy;
step 6: calculating the load-bearing capacity F of a typical cell in a stiffened panelco。
Step 1, giving the average failure stress sigma of the stiffened plate to be calculatedcoAssigning initial values, specifically: pressure loss stress sigma of stiffened plateccGiving the average failure stress sigma to the stiffened plate to be calculatedcoI.e. initial value σco＝σco，σccThe short column with the same stiffened plate section is obtained by a pressure loss test.
And 2, calculating the effective width of the skin, wherein the calculation formula is as follows:
in the formula D11、D12、D22、D66Is the bending stiffness coefficient of the skin; l is the length of the stiffened plate; t is the skin thickness; eskIs the equivalent modulus of the skin;
equivalent axial elastic modulus of the stiffened plate; pi is the circumference ratio; m is the buckling half wave number of the skin, and m is taken as 1,2,3eOf which the smallest beThe result is obtained.
And 3, calculating the turning radius and rho of the stringer and effective width skin combined section, wherein the calculation formula is as follows:
wherein: (EI) bending stiffness of the combined profile;
(EA) is the compressive stiffness of the combined profile.
Step 3, calculating the equivalent modulus of the stringer and effective width skin combined section
The calculation formula is as follows:
Ex＝(EA)/A
wherein: (EA) is the compressive stiffness of the stiffened plate profile;
a is the area of the combined cross section.
Calculating the average failure stress sigma 'of the stringer and effective width skin combined section in the step 4'coThe calculation formula is as follows:
in the formula, L' is the effective column length, and c is the support coefficient of the end part of the stiffened plate.
Calculating the load bearing capacity F of a typical cell in a stiffened panel as described in step 6coThe calculation formula is as follows:
Fco＝σco(Ast+bet)+σcr(b-be)t
in the formula sigmacoAnd beAll the results are the final results obtained by iterative calculation according to the steps 1 to 5; a. thestIs the area of the stringer; b is the stringer axis spacing, σcrIs the local buckling stress of the skin.
The effective column length
The invention has the beneficial effects that: compared with the prior art: the invention provides a method for calculating the effective width of a composite material stiffened wall panel skin, and considers the factors that the modulus of the skin may not be the same as that of a stringer, then calculates the axial pressure failure load by considering the section of a stiffened plate of the effective width skin, and then superposes the bearing capacity of a locally bent skin, and finally obtains the bearing capacity of the whole stiffened plate. Test results show that the result error obtained by calculation according to the method is small and lower than a test value, the result is conservative, and the method is more suitable for engineering application.
Drawings
FIG. 1 is a flow chart of the method of the present invention.
Detailed Description
As shown in fig. 1, a method for calculating the axial compression bearing capacity of a composite material reinforced wall plate comprises the following steps:
step 1: giving the average failure stress sigma of the stiffened panel to be calculatedcoAssigning initial values, specifically: pressure loss stress sigma of stiffened plateccGiving the average failure stress sigma to the stiffened plate to be calculatedcoI.e. initial value σco＝σco，σccThe short column with the same stiffened plate section is obtained through a pressure loss test;
step 2: calculating the effective width b of the skineThe calculation formula is as follows:
in the formula D11、D12、D22、D66Is the bending stiffness coefficient of the skin; l is the length of the stiffened plate; t is the skin thickness; eskIs the equivalent modulus of the skin;
equivalent axial elastic modulus of the stiffened plate; pi is the circumference ratio; m is the buckling half wave number of the skin, and m is taken as 1,2,3eOf which the smallest beThe result is obtained;
and step 3: calculating the gyration radius and rho and equivalent modulus of the stringer and effective width skin combined section
The calculation formula is as follows:
wherein: (EI) bending stiffness of the combined profile;
(EA) is the compressive stiffness of the combined profile;
the calculation formula is as follows: ex＝(EA)/A
Wherein: (EA) is the compressive stiffness of the stiffened plate profile;
a is the area of the combined cross section.
And 4, step 4: calculating mean failure stress σ 'of stringer and effective width skin composite section'coThe calculation formula is as follows:
in the formula, L' is the effective column length, c is the support coefficient of the end part of the stiffened plate, and the effective column length
And 5: judging sigma'coAnd σcoWhether or not | σ is satisfiedco-σ′coEpsilon is less than or equal to | is less than or equal to; if so, then σcoAs the average failure stress of the stiffened plate, if not, the stress is sigma'coAssigned to σcoThen, steps 2 to 5 are repeated until | σ is satisfiedco-σ′coThe | ≦ epsilon, wherein epsilon is a set threshold value used for controlling the calculation precision;
step 6: calculating the load-bearing capacity F of a typical cell in a stiffened panelcoThe calculation formula is as follows:
Fco＝σco(Ast+bet)+σcr(b-be)t
in the formula sigmacoAnd beAll the results are the final results obtained by iterative calculation according to the steps 1 to 5; a. thestIs the area of the stringer; b is the stringer axis spacing, σcrIs the local buckling stress of the skin.
The invention provides a method for calculating the effective width of a composite material stiffened wall panel skin, and considers the factors that the modulus of the skin may not be the same as that of a stringer, then calculates the axial pressure failure load by considering the section of a stiffened plate of the effective width skin, and then superposes the bearing capacity of a locally bent skin, and finally obtains the bearing capacity of the whole stiffened plate. Test results show that the result error obtained by calculation according to the method is small and lower than a test value, the result is conservative, and the method is more suitable for engineering application.
Claims (8)
1. A method for calculating the axial compression bearing capacity of a composite material reinforced wall plate is characterized by comprising the following steps: the method comprises the following steps:
step 1: giving the average failure stress sigma of the stiffened panel to be calculatedcoAssigning an initial value;
step 2: calculating the effective width b of the skine；
And step 3: calculating the gyration radius and rho and equivalent modulus of the stringer and effective width skin combined section
And 4, step 4: calculating mean failure stress σ 'of stringer and effective width skin composite section'co；
And 5: judging sigma'coAnd σcoWhether or not | σ is satisfiedco-σ′coIf | ≦ ε, then σcoAs the average failure stress of the stiffened plate, if not, the stress is sigma'coAssigned to σcoThen, steps 2 to 5 are repeated until | σ is satisfiedco-σ′coThe | ≦ epsilon, wherein epsilon is a set threshold value used for controlling the calculation precision;
step 6: calculating the load-bearing capacity F of a typical cell in a stiffened panelco。
2. The method for calculating the axial compression bearing capacity of the composite material reinforced wall plate according to claim 1, wherein the method comprises the following steps: step 1, giving the average failure stress sigma of the stiffened plate to be calculatedcoAssigning initial values, specifically: pressure loss stress sigma of stiffened plateccGiving the average failure stress sigma to the stiffened plate to be calculatedcoI.e. initial value σco＝σco，σccThe short column with the same stiffened plate section is obtained by a pressure loss test.
3. The method for calculating the axial compression bearing capacity of the composite material reinforced wall plate according to claim 1, wherein the method comprises the following steps: and 2, calculating the effective width of the skin, wherein the calculation formula is as follows:
in the formula D11、D12、D22、D66Is the bending stiffness coefficient of the skin; l is the length of the stiffened plate; t is the skin thickness; eskIs the equivalent modulus of the skin;
equivalent axial elastic modulus of the stiffened plate; pi is the circumference ratio; m is the buckling half wave number of the skin, and m is taken as 1,2,3eOf which the smallest beThe result is obtained.
4. The method for calculating the axial compression bearing capacity of the composite material reinforced wall plate according to claim 1, wherein the method comprises the following steps: and 3, calculating the turning radius and rho of the stringer and effective width skin combined section, wherein the calculation formula is as follows:
wherein: (EI) bending stiffness of the combined profile;
(EA) is the compressive stiffness of the combined profile.
5. The method for calculating the axial compression bearing capacity of the composite material reinforced wall plate according to claim 1, wherein the method comprises the following steps: step 3, calculating the equivalent modulus of the stringer and effective width skin combined section
The calculation formula is as follows:
wherein: (EA) is the compressive stiffness of the stiffened plate profile;
a is the area of the combined cross section.
6. The method for calculating the axial compression bearing capacity of the composite material reinforced wall plate according to claim 1, wherein the method comprises the following steps: calculating average failure stress C 'of stringer and effective width skin combined section in step 4'coThe calculation formula is as follows:
in the formula, L' is the effective column length, and c is the support coefficient of the end part of the stiffened plate.
7. The method for calculating the axial compression bearing capacity of the composite material reinforced wall plate according to claim 1, wherein the method comprises the following steps: calculating the load bearing capacity F of a typical cell in a stiffened panel as described in step 6coThe calculation formula is as follows:
Fco＝σco(Ast+bet)+σcr(b-be)t
in the formula sigmacoAnd beAll the results are the final results obtained by iterative calculation according to the steps 1 to 5; a. thestIs the area of the stringer; b is the stringer axis spacing, σcrIs the local buckling stress of the skin.
8. The method for calculating the axial compression bearing capacity of the composite material reinforced wall plate according to claim 6, wherein the method comprises the following steps: the effective column length
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112699471A (en) * | 2020-12-29 | 2021-04-23 | 中国航空工业集团公司西安飞机设计研究所 | Method and device for calculating effective width of skin under axial compression load of fuselage wallboard |
| CN112699464A (en) * | 2020-12-29 | 2021-04-23 | 中国航空工业集团公司西安飞机设计研究所 | Single-stringer short plate bearing capacity calculation method |
| CN112784369A (en) * | 2020-12-29 | 2021-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Method for checking bearing capacity of composite material reinforced wall plate |
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| CN107506529A (en) * | 2017-08-01 | 2017-12-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Composite Material Stiffened Panel Axial Compression Stability computational methods |
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| CN107506529A (en) * | 2017-08-01 | 2017-12-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Composite Material Stiffened Panel Axial Compression Stability computational methods |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112699471A (en) * | 2020-12-29 | 2021-04-23 | 中国航空工业集团公司西安飞机设计研究所 | Method and device for calculating effective width of skin under axial compression load of fuselage wallboard |
| CN112699464A (en) * | 2020-12-29 | 2021-04-23 | 中国航空工业集团公司西安飞机设计研究所 | Single-stringer short plate bearing capacity calculation method |
| CN112784369A (en) * | 2020-12-29 | 2021-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Method for checking bearing capacity of composite material reinforced wall plate |
| CN112699464B (en) * | 2020-12-29 | 2022-10-11 | 中国航空工业集团公司西安飞机设计研究所 | Single-stringer short plate bearing capacity calculation method |
| CN112784369B (en) * | 2020-12-29 | 2022-10-11 | 中国航空工业集团公司西安飞机设计研究所 | Method for checking bearing capacity of composite material reinforced wall plate |
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