CN114861255A - Structure calculation method based on honeycomb composite board - Google Patents
Structure calculation method based on honeycomb composite board Download PDFInfo
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- CN114861255A CN114861255A CN202210327693.XA CN202210327693A CN114861255A CN 114861255 A CN114861255 A CN 114861255A CN 202210327693 A CN202210327693 A CN 202210327693A CN 114861255 A CN114861255 A CN 114861255A
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Abstract
The invention discloses a structural calculation method based on a honeycomb composite board, which comprises the following steps: calculating a neutral axis of the honeycomb composite board; according to the neutral axis y 0 Calculating the corresponding equivalent bending stiffness of the plate; calculating the equivalent section modulus of the corresponding layer of plate according to the equivalent bending stiffness; and calculating to obtain the equivalent thickness of the corresponding layer of the plate according to the equivalent section modulus correspondingly obtained. The invention solves the problem that the analysis and calculation of the multi-layer honeycomb composite board structure of a honeycomb aluminum board, a stone honeycomb board and the like are restricted by the existing specifications and lack of calculation basis, can accurately carry out mechanical analysis on any multi-layer honeycomb composite board by using the method, is not limited by the material, shape and boundary constraint of the board, can directly judge whether the stress requirement can be met according to the tensile strength of the board because the analyzed strength is of a panel made of a single material, can avoid the trouble that the comprehensive mechanical parameters of the composite board cannot be found, has the advantages of rapidness and convenience, and has better popularization prospect.
Description
Technical Field
The invention relates to the technical field of curtain wall buildings, in particular to a structural calculation method based on a honeycomb composite board.
Background
Composite boards are increasingly used in the curtain wall industry, such as honeycomb stone composite boards, honeycomb composite aluminum boards, honeycomb titanium plates and the like. These new panels are computationally complex relative to conventional panels. Based on current specifications, accurate mechanical analysis of these particular sheets is currently not possible for the following reasons:
1. for the honeycomb composite aluminum plate, the current national specification JGJ 133-. The calculation result is not credible, and potential safety hazards exist or economic benefits are influenced to a certain extent.
2. For the honeycomb stone composite plate, the existing national specification JGJ336-2016 artificial plate curtain wall engineering technical specification provides a corresponding calculation method, but has limitations, for example, the specification only provides an analytical algorithm for supporting the honeycomb stone at 4 points, and the actual project has the situation of supporting at 6 points or even 8 points, so that the expansion needs to be carried out on the basis of the original calculation. The calculation of the equivalent bending stiffness of the honeycomb stone composite board in the specification appendix A describes 2 cases, but only 1 general calculation formula is provided, but the 2 cases cannot be general. The 2 calculation sequences defined by the specification are panel + honeycomb core + panel and panel + panel, respectively, and are determined according to the condition that the stone panel is subjected to positive wind and negative wind. However, since the honeycomb core is located at different positions, the distance from the center of the panel of the layer 2 to the calculation origin is different, so that 1 result is wrong in the same formula calculation.
Therefore, a general calculation method for a structure based on a honeycomb composite board is urgently needed.
Disclosure of Invention
In order to overcome the defects of related products in the prior art, the invention provides a structural calculation method based on a honeycomb composite board.
The invention provides a structural calculation method based on a honeycomb composite board, which comprises the following steps: the method comprises the following steps:
respectively confirming the material of each layer of the current plate material, and setting the plate thickness t of each layer from top to bottom as t 1 、t 2 、t 3 ……t n The elastic modulus E is respectively E 1 、E 2 、E 3 ……E n Taking the outer edge of the lowest side plate as the origin of the calculation coordinate, the distances r from the centroid of each layer of the plate to the origin are r 1 、r 2 、r 3 ……r n ；
Calculating the neutral axis y of the honeycomb composite board 0 Said y is 0 The distance between the neutral axis and the outer edge of the lowest side plate;
according to the neutral axis y 0 Calculating the corresponding equivalent bending rigidity D of the plate e ；
Modulus of equivalent section of ω e Respectively calculating the equivalent section modulus of the uppermost side plate, the equivalent section modulus of the lowermost side plate and the equivalent section modulus corresponding to the ith middle layer plate;
confirming whether the current n layers of composite honeycomb plates are four-point supported honeycomb composite plates or not;
if the current honeycomb composite board is supported by four points, obtaining the equivalent bending rigidity D according to the correspondence e And equivalent section modulus omega e Calculating the deflection of the plate and the strength of the plate of the corresponding layer; if the current honeycomb composite board is not supported by four points, calculating and obtaining the equivalent thickness of the uppermost side board and the lowermost side board and the equivalent thickness of the ith middle layer board, and calculating the deflection of the board and the strength of each layer of board by adopting a finite element modeling method.
In certain embodiments of the invention, the neutral axis y 0 Is calculated by the formula
In certain embodiments of the invention, the equivalents areFlexural rigidity D e Is calculated by the formula
In certain embodiments of the invention, the equivalent section modulus ω e The calculation formulas of (A) and (B) are respectively as follows:
the modulus of equivalent section of the uppermost side plate is
The equivalent section modulus of the lowest side plate is
The equivalent section modulus of the i-th plate is that of the plate on the upper side of the neutral axis
The lower side of the neutral axis of the plate is
In some embodiments of the invention, the four-point supports the deflection d of the sheet f Is calculated by the formula
Wherein mu is a deflection coefficient, eta is a reduction coefficient, b is the length of the long side of the plate, and w is a load standard value.
In some embodiments of the invention, the strength σ of the four-point support sheet is calculated by the formula
Wherein m is a bending moment coefficient, b is the length of the long side of the plate, and w is a load design value.
In certain embodiments of the invention, the equivalent thickness t e Is calculated by the formula
Namely, it is
I e The moment of inertia is taken as the 1mm microsegment.
Compared with the prior art, the invention has the following advantages:
the structural calculation method based on the honeycomb composite board solves the problems that structural analysis and calculation of multilayer honeycomb composite boards such as a honeycomb aluminum board, a stone honeycomb board and the like are restricted by the existing specifications and lack of calculation basis, can accurately perform mechanical analysis on any multilayer honeycomb composite board by using the method, is not limited by the material, shape and boundary of the board, has the advantages of rapidness and convenience, is a panel made of a single material in strength, can directly judge whether the stress requirement can be met according to the tensile strength of the panel, can avoid the trouble that comprehensive mechanical parameters of the composite board cannot be found, and has accurate and reliable calculation results after being compared and calculated by software.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of an embodiment of a structural calculation method based on a honeycomb composite board according to the present invention;
FIG. 2 is a schematic structural diagram with a neutral axis of one embodiment of the structural calculation method based on the honeycomb composite board according to the invention;
FIG. 3 is a graph of strength calculated using SAP2000 analysis using a first ply equivalent thickness;
FIG. 4 is a graph of strength calculated using SAP2000 analysis using the equivalent thickness of a second ply;
FIG. 5 is a graph of strength calculated using SAP2000 analysis using the equivalent thickness of a fourth ply;
figure 6 is a schematic view of deflection calculated using SAP2000 analysis using the first ply equivalent thickness.
Detailed Description
In order to make the technical solutions of the present invention better understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the described embodiments are merely illustrative of some, but not all, of the embodiments of the invention, and that the preferred embodiments of the invention are shown in the drawings. This invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein, but rather should be construed as broadly as the present disclosure is set forth in order to provide a more thorough understanding thereof.
The structural calculation method based on the honeycomb composite board comprises the following steps:
step 1: respectively confirming the material of each layer of the current plate material, and setting the plate thickness t of each layer from top to bottom as t 1 、t 2 、t 3 ……t n The elastic modulus E is respectively E 1 、E 2 、E 3 ……E n Taking the outer edge of the lowest side plate as the origin of the calculation coordinate, the distances r from the centroid of each layer of the plate to the origin are r 1 、r 2 、r 3 ……r n ；
Step 2: calculating the neutral axis y of the honeycomb composite board 0 Said y is 0 The distance between the neutral axis and the outer edge of the lowest side plate;
and step 3: according to the neutral axis y 0 Calculating the corresponding equivalent bending rigidity D of the plate e ；
And 4, step 4: modulus of equivalent section of ω e Respectively calculating the equivalent section modulus of the uppermost side plate, the equivalent section modulus of the lowermost side plate and the equivalent section modulus corresponding to the ith middle layer plate;
and 5: confirming whether the current n layers of composite honeycomb plates are four-point supported honeycomb composite plates or not;
step 6: if the current honeycomb composite board is supported by four points, obtaining the equivalent bending rigidity D according to the correspondence e And equivalent section modulus omega e Calculating the deflection of the plate and the strength of the plate of the corresponding layer; if the current honeycomb composite board is not supported by four points, calculating and obtaining the equivalent thickness of the uppermost side board and the lowermost side board and the equivalent thickness of the ith middle layer board, and calculating the deflection of the board and the strength of each layer of board by adopting a finite element modeling method.
Wherein, in the embodiment of the present invention, the neutral axis y 0 Is calculated by the formula
The equivalent bending stiffness D e Is calculated by the formula
The equivalent section modulus omega e The calculation formulas of (A) and (B) are respectively as follows:
the modulus of equivalent section of the uppermost side plate is
The equivalent section modulus of the lowest side plate is
The equivalent section modulus of the i-th plate is that of the plate on the upper side of the neutral axis
The lower side of the neutral axis of the plate is
Four point support plate deflection d f Is calculated by the formula
Wherein mu is a deflection coefficient, eta is a reduction coefficient, b is the length of the long side of the plate, and w is a load standard value.
The stress intensity sigma of the four-point supporting plate is calculated by the formula
Wherein m is a bending moment coefficient, b is the length of the long side of the plate, and w is a load design value.
The equivalent thickness t e Is calculated by the formula
Namely, it is
I e The moment of inertia is taken as the 1mm microsegment.
In step 6, the calculation and verification of the structural parameters according to the embodiment of the present invention may be calculated by using any finite element analysis software, for example, software with the same function such as SAP 2000.
The following is described in detail with reference to the following examples, which are shown in FIGS. 1-2:
four-point support is adopted, and the four-point support comprises 6 layers from top to bottom, namely a stone panel, a back plate bonded with stone, an aluminum honeycomb core plate, an intermediate layer aluminum plate, an aluminum honeycomb core plate and a back plate outer panel in sequence;
then, taking the outer edge of the lowest side plate (outer panel of the back plate) as a calculation origin of coordinates, and the corresponding related parameters of each layer of plate are as follows:
first layer, E 1 ＝80000MPa....t 1 ＝5mm....r 1 ＝35.5mm；
A second layer, E 2 ＝70000MPa....t 2 ＝1mm....r 2 ＝32.5mm；
Third layer, E 3 ＝0MPa....t 3 ＝18mm....r 3 ＝23mm；
Fourth layer, E 4 ＝70000MPa....t 4 ＝2mm....r 4 ＝13mm；
Fifth layer, E 5 ＝0MPa....t 5 ＝10mm....r 5 ＝7mm；
Sixth layer, E 6 ＝70000MPa....t 6 ＝2mm....r 6 ＝1mm；
It should be noted that, when the elastic model of the aluminum honeycomb core is small, E may be 0.
Based on the foregoing parameters, the distance of the neutral axis from the outer edge of the lowermost panel is calculated as
The first layer is located on the upper side of the neutral axis, and the equivalent section modulus of the first layer is
The second layer is located on the upper side of the neutral axis, and the equivalent section modulus of the second layer is
The fourth layer is positioned at the lower side of the neutral axis, and the equivalent section modulus of the fourth layer is
If the size of the panel is 1000mm multiplied by 500mm, the load is 2 kPa; the deflection coefficient mu is 0.01417, the bending moment coefficient m is 0.13, the reduction coefficient eta is 0.9464, and the length b of the long side is 1000 mm;
the stress of the first laminate is:
the stress of the second laminate is:
the stress of the fourth ply is:
computingObtaining the deflection of the panel:
the calculation of the equivalent thickness was verified using SAP 2000:
the equivalent thickness when calculating the first laminate is:
E 1 80000MPa, first panel SAP2000 stress results as shown in fig. 3: 1.869 MPa.
The equivalent thickness when calculating the second laminate is:
E 2 70000MPa, second ply SAP2000 stress results as shown in fig. 4: 1.023 MPa.
The equivalent thickness when calculating the fourth ply is:
E 4 70000MPa, fourth ply SAP2000 stress results as shown in fig. 5: 1.529 MPa.
Using the equivalent thickness t of the first ply e1 28.918mm and E 1 Deflection was calculated at 80000MPa, as shown in FIG. 6, and the deflection results for the plate: 0.172 mm.
It should be noted that the deflection can only be calculated by modeling the equivalent thickness of the uppermost or lowermost panel of the multi-layer composite panel, since only the equivalent thickness of the outermost panel is equivalent to the overall neutral axis of the multi-layer composite panel.
Comparison can confirm that the data obtained by the algorithm of the present embodiment is consistent with the software analysis results with equivalent thickness (slight difference is because the algorithm of the present embodiment ignores the poisson's ratio of the material).
The structural calculation method based on the honeycomb composite board solves the problems that structural analysis and calculation of multilayer honeycomb composite boards such as a honeycomb aluminum board, a stone honeycomb board and the like are restricted by the existing specifications and lack of calculation basis, can accurately perform mechanical analysis on any multilayer honeycomb composite board by using the method, is not limited by the material, shape and boundary of the board, has the advantages of rapidness and convenience, is a panel made of a single material in strength, can directly judge whether the stress requirement can be met according to the tensile strength of the panel, can avoid the trouble that comprehensive mechanical parameters of the composite board cannot be found, and has accurate and reliable calculation results after being compared and calculated by software.
Those not described in detail in this specification are within the skill of the art. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described in the foregoing detailed description, or equivalent changes may be made in some of the features of the embodiments. All equivalent structures made by using the contents of the specification and the attached drawings of the invention can be directly or indirectly applied to other related technical fields, and are also within the protection scope of the patent of the invention.
Claims (7)
1. A structure calculation method based on a honeycomb composite board is characterized by comprising the following steps:
respectively confirming the material of each layer of the current plate material, and setting the plate thickness t of each layer from top to bottom as t 1 、t 2 、t 3 ……t n The elastic modulus E is respectively E 1 、E 2 、E 3 ……E n Taking the outer edge of the lowest side plate as the origin of the calculation coordinate, the distances r from the centroid of each layer of the plate to the origin are r 1 、r 2 、r 3 ……r n ；
Calculating the neutral axis y of the honeycomb composite board 0 Said y is 0 The distance between the neutral axis and the outer edge of the lowest side plate;
according to the neutral axis y 0 Calculating the corresponding equivalent bending stiffness of the sheetD e ；
Modulus of equivalent section of ω e Respectively calculating the equivalent section modulus of the uppermost side plate, the equivalent section modulus of the lowermost side plate and the equivalent section modulus corresponding to the ith middle layer plate;
confirming whether the current n layers of composite honeycomb plates are four-point supported honeycomb composite plates or not;
if the current honeycomb composite board is supported by four points, obtaining the equivalent bending rigidity D according to the correspondence e And equivalent section modulus omega e Calculating the deflection of the plate and the strength of the plate of the corresponding layer; if the current honeycomb composite board is not supported by four points, calculating and obtaining the equivalent thickness of the uppermost side board and the lowermost side board and the equivalent thickness of the ith middle layer board, and calculating the deflection of the board and the strength of each layer of board by adopting a finite element modeling method.
2. The method of calculating a structure based on a honeycomb composite panel according to claim 1, wherein: the neutral axis y 0 Is calculated by the formula
3. The method of calculating a structure based on a honeycomb composite panel according to claim 2, wherein: the equivalent bending stiffness D e Is calculated by the formula
4. The method of calculating a honeycomb composite panel-based structure according to claim 3, wherein the equivalent section modulus ω is e The calculation formulas of (A) and (B) are respectively as follows:
the modulus of equivalent section of the uppermost side plate is
The equivalent section modulus of the lowest side plate is
The equivalent section modulus of the i-th plate is that of the plate on the upper side of the neutral axis
The lower side of the neutral axis of the plate is
5. The cellular composite board based structure calculation method according to claim 3, wherein: four point support plate deflection d f Is calculated by the formula
Wherein mu is a deflection coefficient, eta is a reduction coefficient, b is the length of the long side of the plate, and w is a load standard value.
6. The method of calculating a structure based on a honeycomb composite panel according to claim 4, wherein: the strength sigma of the four-point supporting plate is calculated by the formula
Wherein m is a bending moment coefficient, b is the length of the long side of the plate, and w is a load design value.
7. The method of calculating a structure based on a honeycomb composite panel according to claim 4, wherein: the equivalent thickness t e Is calculated by the formula
Namely, it is
I e The moment of inertia is taken as the 1mm microsegment.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117292778A (en) * | 2023-11-24 | 2023-12-26 | 中国石油大学(华东) | Method for calculating mechanical properties of gradient hole anode of solid oxide fuel cell |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117292778A (en) * | 2023-11-24 | 2023-12-26 | 中国石油大学(华东) | Method for calculating mechanical properties of gradient hole anode of solid oxide fuel cell |
| CN117292778B (en) * | 2023-11-24 | 2024-02-20 | 中国石油大学(华东) | Method for calculating mechanical properties of gradient hole anode of solid oxide fuel cell |
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