CN114861255A - A structural calculation method based on honeycomb composite panels - Google Patents

A structural calculation method based on honeycomb composite panels Download PDF

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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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肖波
胡忠明
朱裕良
邱念
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Wuhan Lingyun Architectural Decoration Engineering Co ltd
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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

一种基于蜂窝复合板材的结构计算方法A structural calculation method based on honeycomb composite panels

技术领域technical field

本发明涉及幕墙建筑技术领域，尤其涉及一种基于蜂窝复合板材的结构计算方法。The invention relates to the technical field of curtain wall construction, in particular to a structure calculation method based on a honeycomb composite board.

背景技术Background technique

复合板材在幕墙行业中的应用越来越广泛，例如蜂窝石材复合板、蜂窝复合铝板、蜂窝钛金板等。相对传统的板材来说，这些新型板材的计算比较复杂。基于现行规范，对这些特殊的板材目前还无法进行精确的力学分析，原因如下：The application of composite panels in the curtain wall industry is more and more extensive, such as honeycomb stone composite panels, honeycomb composite aluminum panels, honeycomb titanium gold panels, etc. Compared with traditional plates, the calculation of these new plates is more complicated. Based on current specifications, accurate mechanical analysis of these special sheets is not currently possible for the following reasons:

1、对于蜂窝复合铝板，现行国家规范JGJ 133-2001《金属与石材幕墙工程技术规范》给出了材料在不同厚度下的弹性模量和泊松比，但是抗拉强度只提供了20mm厚的数据，其他厚度的强度无从得知，便需要厂家配合做检测报告，但是报告里面也不一定能找到计算需要的强度，即使有往往也与理论上偏差非常大，不同厂家之间提供的结果也是有差异的。导致计算结果不太可信，一定程度上会存在安全隐患或影响经济效益。1. For honeycomb composite aluminum panels, the current national standard JGJ 133-2001 "Technical Specifications for Metal and Stone Curtain Wall Engineering" gives the elastic modulus and Poisson's ratio of the material under different thicknesses, but the tensile strength only provides 20mm thick data , the strength of other thicknesses cannot be known, so the manufacturer needs to cooperate with the test report, but the strength required for the calculation may not be found in the report. Even if there is, there is often a large deviation from the theory. Difference. As a result, the calculation results are unreliable, and to a certain extent, there will be security risks or economic benefits.

2、对于蜂窝石材复合板，现行国家规范JGJ336-2016《人造板材幕墙工程技术规范》提供了相应的计算方法，但是存在局限性，例如，规范中只给了4点支撑蜂窝石材的解析算法，而实际项目中存在6点甚至8点支撑的情况，因此需要在原计算基础上进行拓展。该规范附录A中对蜂窝石材复合板的等效弯曲刚度计算描述了2种情况，却仅提供了1个通用计算公式，但这2种情况并不能通用。规范定义的2种计算顺序分别为“面板+面板+蜂窝芯+面板”、“面板+蜂窝芯+面板+面板”，是根据石材面板受正、负风来决定的。但是由于蜂窝芯所处的位置不同，会导致第2层面板中心到计算原点的距离不一样，所以按同一个公式计算会有1种结果是错误的。2. For honeycomb stone composite panels, the current national standard JGJ336-2016 "Technical Specifications for Man-made Panel Curtain Wall Engineering" provides corresponding calculation methods, but there are limitations. In actual projects, there are 6 or even 8 points of support, so it needs to be expanded on the basis of the original calculation. Appendix A of the specification describes two cases for the calculation of the equivalent bending stiffness of honeycomb stone composite panels, but only provides a general calculation formula, but these two cases are not universal. The two calculation sequences defined by the specification are "panel + panel + honeycomb core + panel", "panel + honeycomb core + panel + panel", which are determined according to the positive and negative wind of the stone panel. However, due to the different positions of the honeycomb core, the distance from the center of the second layer of the panel to the calculation origin will be different, so there will be one result that is wrong if calculated by the same formula.

因此，当前亟待出现一种基于蜂窝复合板材的结构通用计算方法。Therefore, there is an urgent need for a general calculation method for the structure based on honeycomb composite panels.

发明内容SUMMARY OF THE INVENTION

为了克服现有技术中相关产品的不足，本发明提出一种基于蜂窝复合板材的结构计算方法。In order to overcome the deficiencies of related products in the prior art, the present invention proposes a structure calculation method based on a honeycomb composite board.

本发明提供了一种基于蜂窝复合板材的结构计算方法，包括：如下步骤：The invention provides a structure calculation method based on a honeycomb composite board, comprising the following steps:

分别确认当前的板材各层的材质，设其从上至下各层的板厚t依次为t1、t2、t3……tn，弹性模量E依次分别为E1、E2、E3……En，以最下侧板外缘为计算坐标原点，各层的板材形心到原点的距离r依次分别为r1、r2、r3……rn；Confirm the material of each layer of the current plate respectively, set the thickness t of each layer from top to bottom as t 1 , t 2 , t 3 ...... t n , and the elastic modulus E as E 1 , E 2 , E 3 ......E n , take the outer edge of the lowermost plate as the origin of the calculated coordinates, the distance r from the centroid of the plate of each layer to the origin is respectively r 1 , r 2 , r 3 ...... rn ;

计算所述蜂窝复合板材的中性轴y0，所述y0为中性轴距最下侧板外缘的距离；Calculate the neutral axis y 0 of the honeycomb composite plate, and the y 0 is the distance between the neutral axis and the outer edge of the lowermost side plate;

根据所述中性轴y0计算板材对应的等效弯曲刚度De；Calculate the equivalent bending stiffness D e corresponding to the plate according to the neutral axis y 0 ;

等效截面模量为ωe，分别计算最上侧板的等效截面模量、最下侧板的等效截面模量以及中间第i层板对应的等效截面模量；The equivalent section modulus is ω e , and 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 i-th layer plate in the middle are calculated respectively;

确认当前n层复合的蜂窝板材是否为四点支撑的蜂窝复合板材；Confirm whether the current n-layer composite honeycomb board is a four-point supported honeycomb composite board;

若当前为四点支撑的蜂窝复合板材，则根据对应获取的等效弯曲刚度De和等效截面模量ωe，计算板材的挠度以及对应层板材的强度；若当前为非四点支撑的蜂窝复合板材，则计算获取最上侧板和最下侧板的的等效厚度以及中间第i层板的等效厚度，采用有限元建模的方法计算板材的挠度和各层板材的强度。If it is a four-point supported honeycomb composite plate, the deflection of the plate and the strength of the corresponding layer plate are calculated according to the correspondingly obtained equivalent bending stiffness D e and equivalent section modulus ω e ; if the current one is not four-point supported For honeycomb composite panels, the equivalent thicknesses of the uppermost and lowermost side panels and the equivalent thickness of the i-th layer in the middle are calculated and obtained, and the finite element modeling method is used to calculate the deflection of the panels and the strength of each layer of panels.

在本发明的某些实施方式中，所述中性轴y0的计算公式为

Figure BDA0003572143360000021
In some embodiments of the present invention, the calculation formula of the neutral axis y 0 is:
Figure BDA0003572143360000021

在本发明的某些实施方式中，所述等效弯曲刚度De的计算公式为

Figure BDA0003572143360000022
In some embodiments of the present invention, the calculation formula of the equivalent bending stiffness De is:
Figure BDA0003572143360000022

在本发明的某些实施方式中，所述等效截面模量ωe的计算公式分别为：In some embodiments of the present invention, the calculation formulas of the equivalent section modulus ω e are:

最上侧板的等效截面模量为

Figure BDA0003572143360000031
The equivalent section modulus of the uppermost side plate is
Figure BDA0003572143360000031

最下侧板的等效截面模量为

Figure BDA0003572143360000032
The equivalent section modulus of the lowermost side plate is
Figure BDA0003572143360000032

第i层板的等效截面模量，板材在中性轴上侧的为

Figure BDA0003572143360000033
板材在中性轴下侧的为
Figure BDA0003572143360000034
The equivalent section modulus of the i-th layer plate, the plate on the upper side of the neutral axis is
Figure BDA0003572143360000033
The plate on the lower side of the neutral axis is
Figure BDA0003572143360000034

在本发明的某些实施方式中，四点支撑板材的挠度df的计算公式为

Figure BDA0003572143360000035
其中，μ为挠度系数，η为折减系数，b为板材长边长度，w为荷载标准值。In some embodiments of the present invention, the formula for calculating the deflection d f of the four-point support plate is:
Figure BDA0003572143360000035
Among them, μ is the deflection coefficient, η is the reduction coefficient, b is the length of the long side of the plate, and w is the standard value of the load.

在本发明的某些实施方式中，四点支撑板材的强度σ的计算公式为

Figure BDA0003572143360000036
其中，m为弯矩系数，b为板材长边长度，w为荷载设计值。In some embodiments of the present invention, the formula for calculating the strength σ of the four-point support plate is:
Figure BDA0003572143360000036
Among them, m is the bending moment coefficient, b is the length of the long side of the plate, and w is the design load value.

在本发明的某些实施方式中，所述等效厚度te的计算公式为

Figure BDA0003572143360000037
即
Figure BDA0003572143360000038
Ie为取1mm微段的惯性矩。In some embodiments of the present invention, the calculation formula of the equivalent thickness t e is:
Figure BDA0003572143360000037
which is
Figure BDA0003572143360000038
I e is the moment of inertia of a micro-segment of 1 mm.

与现有技术相比，本发明有以下优点：Compared with the prior art, the present invention has the following advantages:

本发明实施例所述基于蜂窝复合板材的结构计算方法解决了蜂窝铝板、石材蜂窝板等多层蜂窝复合板结构分析计算受现有规范制约，缺乏计算依据的问题，使用此方法可以精确的对任意多层蜂窝复合板进行力学分析，不受板材材质、形状及边界约束的限制，而且分析出来的强度是单一材质面板的，能够直接根据其抗拉强度判断是否可以满足受力要求，可免去找不到复合板综合力学参数的麻烦，具有快速便捷的优点，且该计算方法经过软件的比较验算，证实其计算结果准确可靠，为多层蜂窝复合板的结构设计找到了一种全新的、通用的方法，具有较好的推广前景。The structural calculation method based on the honeycomb composite plate described in the embodiment of the present invention solves the problem that the structural analysis and calculation of the multi-layer honeycomb composite plate such as honeycomb aluminum plate and stone honeycomb plate is restricted by the existing specifications and lacks calculation basis. The mechanical analysis of any multi-layer honeycomb composite panel is not limited by the material, shape and boundary constraints of the panel, and the strength analyzed is that of a single-material panel, which can directly determine whether it can meet the stress requirements according to its tensile strength. It has the advantages of being fast and convenient to avoid the trouble of finding the comprehensive mechanical parameters of the composite panel, and the calculation method has been verified by the software to verify that the calculation results are accurate and reliable. , a general method, and has a good promotion prospect.

附图说明Description of drawings

为了更清楚地说明本发明实施例中的技术方案，下面将对实施例中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他的附图。In order to illustrate the technical solutions in the embodiments of the present invention more clearly, the following briefly introduces the drawings required in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can also be obtained from these drawings without any creative effort.

图1为本发明所述基于蜂窝复合板材的结构计算方法一个实施例的结构示意图；FIG. 1 is a schematic structural diagram of an embodiment of the structure calculation method based on the honeycomb composite board according to the present invention;

图2为本发明所述基于蜂窝复合板材的结构计算方法一个实施例带中性轴的结构示意图；FIG. 2 is a schematic structural diagram with a neutral axis according to an embodiment of the structure calculation method based on the honeycomb composite board according to the present invention;

图3为利用第一层板等效厚度采用SAP2000分析计算的强度示意图；Figure 3 is a schematic diagram of the strength calculated by SAP2000 analysis using the equivalent thickness of the first layer;

图4为利用第二层板等效厚度采用SAP2000分析计算的强度示意图；Figure 4 is a schematic diagram of the strength calculated by SAP2000 analysis using the equivalent thickness of the second layer;

图5为利用第四层板等效厚度采用SAP2000分析计算的强度示意图；Figure 5 is a schematic diagram of the strength calculated by SAP2000 analysis using the equivalent thickness of the fourth layer board;

图6为利用第一层板等效厚度采用SAP2000分析计算的挠度示意图。Figure 6 is a schematic diagram of the deflection calculated by SAP2000 analysis using the equivalent thickness of the first layer.

具体实施方式Detailed ways

为了使本技术领域的人员更好地理解本发明方案，下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述。显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例，附图中给出了本发明的较佳实施例。本发明可以以许多不同的形式来实现，并不限于本文所描述的实施例，相反地，提供这些实施例的目的是使对本发明的公开内容的理解更加透彻全面。In order for those skilled in the art to better understand the solutions of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of, but not all, embodiments of the present invention, and preferred embodiments of the present invention are shown in the accompanying drawings. The present invention may be embodied in many different forms and is not limited to the embodiments described herein, but rather, these embodiments are provided so that a thorough understanding of the present disclosure will be provided.

本发明实施例所述基于蜂窝复合板材的结构计算方法包括如下步骤：The structural calculation method based on the honeycomb composite board according to the embodiment of the present invention includes the following steps:

步骤1：分别确认当前的板材各层的材质，设其从上至下各层的板厚t依次为t1、t2、t3……tn，弹性模量E依次分别为E1、E2、E3……En，以最下侧板外缘为计算坐标原点，各层的板材形心到原点的距离r依次分别为r1、r2、r3……rn；Step 1: Confirm the material of each layer of the current sheet, and set the thickness t of each layer from top to bottom as t 1 , t 2 , t 3 ...... t n , and the elastic modulus E as E 1 , E 2 , E 3 ...... E n , take the outer edge of the lowermost side plate as the origin of the calculated coordinates, and the distance r from the plate centroid of each layer to the origin is r 1 , r 2 , r 3 ...... rn , respectively;

步骤2：计算所述蜂窝复合板材的中性轴y0，所述y0为中性轴距最下侧板外缘的距离；Step 2: Calculate the neutral axis y 0 of the honeycomb composite plate, and the y 0 is the distance between the neutral axis and the outer edge of the lowermost side plate;

步骤3：根据所述中性轴y0计算板材对应的等效弯曲刚度De；Step 3: Calculate the equivalent bending stiffness D e corresponding to the plate according to the neutral axis y 0 ;

步骤4：等效截面模量为ωe，分别计算最上侧板的等效截面模量、最下侧板的等效截面模量以及中间第i层板对应的等效截面模量；Step 4: The equivalent section modulus is ω e , and 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 i-th layer plate in the middle are calculated respectively;

步骤5：确认当前n层复合的蜂窝板材是否为四点支撑的蜂窝复合板材；Step 5: Confirm whether the current n-layer composite honeycomb board is a four-point supported honeycomb composite board;

步骤6：若当前为四点支撑的蜂窝复合板材，则根据对应获取的等效弯曲刚度De和等效截面模量ωe，计算板材的挠度以及对应层板材的强度；若当前为非四点支撑的蜂窝复合板材，则计算获取最上侧板和最下侧板的的等效厚度以及中间第i层板的等效厚度，采用有限元建模的方法计算板材的挠度和各层板材的强度。Step 6: If the current four-point-supported honeycomb composite plate is used, calculate the deflection of the plate and the strength of the corresponding layer plate according to the correspondingly obtained equivalent bending stiffness D e and equivalent section modulus ω e ; For point-supported honeycomb composite panels, the equivalent thicknesses of the uppermost and lowermost panels and the equivalent thickness of the i-th layer in the middle are calculated and obtained, and the finite element modeling method is used to calculate the deflection of the panels and the strength.

其中，在本发明实施例中，所述中性轴y0的计算公式为

Figure BDA0003572143360000051
Wherein, in the embodiment of the present invention, the calculation formula of the neutral axis y 0 is:
Figure BDA0003572143360000051

所述等效弯曲刚度De的计算公式为

Figure BDA0003572143360000052
The calculation formula of the equivalent bending stiffness D e is:
Figure BDA0003572143360000052

所述等效截面模量ωe的计算公式分别为：The calculation formulas of the equivalent section modulus ω e are:

最上侧板的等效截面模量为

Figure BDA0003572143360000053
The equivalent section modulus of the uppermost side plate is
Figure BDA0003572143360000053

最下侧板的等效截面模量为

Figure BDA0003572143360000054
The equivalent section modulus of the lowermost side plate is
Figure BDA0003572143360000054

第i层板的等效截面模量，板材在中性轴上侧的为

Figure BDA0003572143360000055
板材在中性轴下侧的为
Figure BDA0003572143360000061
The equivalent section modulus of the i-th layer plate, the plate on the upper side of the neutral axis is
Figure BDA0003572143360000055
The plate on the lower side of the neutral axis is
Figure BDA0003572143360000061

四点支撑板材的挠度df的计算公式为

Figure BDA0003572143360000062
其中，μ为挠度系数，η为折减系数，b为板材长边长度，w为荷载标准值。The formula for calculating the deflection d f of the four-point support plate is:
Figure BDA0003572143360000062
Among them, μ is the deflection coefficient, η is the reduction coefficient, b is the length of the long side of the plate, and w is the standard value of the load.

四点支撑板材的应力强度σ的计算公式为

Figure BDA0003572143360000063
其中，m为弯矩系数，b为板材长边长度，w为荷载设计值。The formula for calculating the stress strength σ of the four-point support plate is:
Figure BDA0003572143360000063
Among them, m is the bending moment coefficient, b is the length of the long side of the plate, and w is the design load value.

所述等效厚度te的计算公式为

Figure BDA0003572143360000064
即
Figure BDA0003572143360000065
Ie为取1mm微段的惯性矩。The calculation formula of the equivalent thickness t e is:
Figure BDA0003572143360000064
which is
Figure BDA0003572143360000065
I e is the moment of inertia of a micro-segment of 1 mm.

上述步骤6中，本发明实施例的结构参数的计算验证可以利用任意有限元分析软件计算，例如SAP2000等相同功能的软件。In the above step 6, the calculation and verification of the structural parameters in 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 SAP2000.

以下结合实施例进行具体说明，结合图1-2所示：The specific description is given below in conjunction with the embodiments, as shown in Figures 1-2:

采用四点支撑，从上往下包括6层，依次分别为石材面板、与石材粘接的背板、铝蜂窝芯板、中间层铝板、铝蜂窝芯板以及背板外面板；It adopts four-point support, including 6 layers from top to bottom, which are the stone panel, the back panel bonded to the stone, the aluminum honeycomb core panel, the middle layer aluminum panel, the aluminum honeycomb core panel and the outer panel of the back panel;

则以最下侧板(背板外面板)外缘为计算坐标原点，各层板材对应的相关参数依次为：Then take the outer edge of the lowermost side panel (outer panel of the back panel) as the origin of the calculated coordinates, and the relevant parameters corresponding to each layer of panels are as follows:

第一层，E1＝80000MPa....t1＝5mm....r1＝35.5mm；The first layer, E 1 =80000MPa....t 1 =5mm....r 1 =35.5mm;

第二层，E2＝70000MPa....t2＝1mm....r2＝32.5mm；The second layer, E 2 =70000MPa....t 2 =1mm....r 2 =32.5mm;

第三层，E3＝0MPa....t3＝18mm....r3＝23mm；The third layer, E 3 =0MPa....t 3 =18mm....r 3 =23mm;

第四层，E4＝70000MPa....t4＝2mm....r4＝13mm；The fourth layer, E 4 =70000MPa....t 4 =2mm....r 4 =13mm;

第五层，E5＝0MPa....t5＝10mm....r5＝7mm；The fifth layer, E 5 =0MPa....t 5 =10mm....r 5 =7mm;

第六层，E6＝70000MPa....t6＝2mm....r6＝1mm；The sixth layer, E 6 =70000MPa....t 6 =2mm....r 6 =1mm;

需要说明的是，在铝蜂窝芯弹性模型较小时，E可取0。It should be noted that when the elastic model of the aluminum honeycomb core is small, E can be taken as 0.

根据前述参数，计算中性轴距最下侧板外缘的距离为

Figure BDA0003572143360000071
According to the aforementioned parameters, the distance between the neutral wheel and the outer edge of the lowermost side plate is calculated as
Figure BDA0003572143360000071

第一层位于中性轴上侧，则第一层的等效截面模量为

Figure BDA0003572143360000072
The first layer is located on the upper side of the neutral axis, then the equivalent section modulus of the first layer is
Figure BDA0003572143360000072

第二层位于中性轴上侧，则第二层的等效截面模量为

Figure BDA0003572143360000073
The second layer is located on the upper side of the neutral axis, then the equivalent section modulus of the second layer is
Figure BDA0003572143360000073

第四层位于中性轴下侧，则第四层的等效截面模量为

Figure BDA0003572143360000074
The fourth layer is located on the lower side of the neutral axis, then the equivalent section modulus of the fourth layer is
Figure BDA0003572143360000074

若面板的尺寸为1000mm×500mm，荷载为2kPa；挠度系数μ＝0.01417，弯矩系数m＝0.13，折减系数η＝0.9464，长边长度b＝1000mm；If the size of the panel is 1000mm×500mm, the load is 2kPa; the deflection coefficient μ=0.01417, the bending moment coefficient m=0.13, the reduction coefficient η=0.9464, and the long side length b=1000mm;

第一层板的应力为：

Figure BDA0003572143360000075
The stress of the first layer board is:
Figure BDA0003572143360000075

第二层板的应力为：

Figure BDA0003572143360000076
The stress of the second layer board is:
Figure BDA0003572143360000076

第四层板的应力为：

Figure BDA0003572143360000077
The stress of the fourth layer is:
Figure BDA0003572143360000077

计算得到面板挠度：

Figure BDA0003572143360000078
Calculate the panel deflection:
Figure BDA0003572143360000078

采用SAP2000对等效厚度的计算进行验证：The calculation of equivalent thickness is verified by SAP2000:

计算第一层板时等效厚度为：

Figure BDA0003572143360000079
E1＝80000MPa，如图3所示，第一层板SAP2000应力结果：1.869MPa。The equivalent thickness when calculating the first layer is:
Figure BDA0003572143360000079
E 1 =80000MPa, as shown in Figure 3, the stress result of SAP2000 of the first layer board: 1.869MPa.

计算第二层板时等效厚度为：

Figure BDA00035721433600000710
E2＝70000MPa，如图4所示，第二层板SAP2000应力结果：1.023MPa。The equivalent thickness when calculating the second layer is:
Figure BDA00035721433600000710
E 2 =70000MPa, as shown in Figure 4, the stress result of SAP2000 of the second layer board: 1.023MPa.

计算第四层板时等效厚度为：

Figure BDA0003572143360000081
E4＝70000MPa，如图5所示，第四层板SAP2000应力结果：1.529MPa。The equivalent thickness when calculating the fourth layer is:
Figure BDA0003572143360000081
E 4 =70000MPa, as shown in Figure 5, the stress result of SAP2000 of the fourth layer board: 1.529MPa.

利用第一层板的等效厚度te1＝28.918mm和E1＝80000MPa计算挠度，如图6所示，板的挠度结果：0.172mm。The deflection is calculated using the equivalent thickness t e1 =28.918mm and E 1 =80000MPa of the first layer board, as shown in Figure 6, the deflection result of the board: 0.172mm.

需要特别说明，只能取多层复合板的最上侧或最下侧板的等效厚度建模计算挠度，因为只有最外侧板的等效厚度是根据多层复合板的整体中性轴等效而来。It needs to be specially explained that only the equivalent thickness of the uppermost or lowermost side plate of the multi-layer composite plate can be used to model the deflection, because only the equivalent thickness of the outermost plate is equivalent to the overall neutral axis of the multi-layer composite plate. Come.

对比可以确认通过本发明实施例的算法获取的数据与取等效厚度的软件分析结果一致(细微差别是因为本发明实施例的算法忽略了材料的泊松比)。By comparison, it can be confirmed that the data obtained by the algorithm of the embodiment of the present invention is consistent with the software analysis result of taking the equivalent thickness (the slight difference is because the algorithm of the embodiment of the present invention ignores the Poisson's ratio of the material).

本发明实施例所述基于蜂窝复合板材的结构计算方法解决了蜂窝铝板、石材蜂窝板等多层蜂窝复合板结构分析计算受现有规范制约，缺乏计算依据的问题，使用此方法可以精确的对任意多层蜂窝复合板进行力学分析，不受板材材质、形状及边界约束的限制，而且分析出来的强度是单一材质面板的，能够直接根据其抗拉强度判断是否可以满足受力要求，可免去找不到复合板综合力学参数的麻烦，具有快速便捷的优点，且该计算方法经过软件的比较验算，证实其计算结果准确可靠，为多层蜂窝复合板的结构设计找到了一种全新的、通用的方法，具有较好的推广前景。The structural calculation method based on the honeycomb composite plate described in the embodiment of the present invention solves the problem that the structural analysis and calculation of the multi-layer honeycomb composite plate such as honeycomb aluminum plate and stone honeycomb plate is restricted by the existing specifications and lacks calculation basis. The mechanical analysis of any multi-layer honeycomb composite panel is not limited by the material, shape and boundary constraints of the panel, and the strength analyzed is that of a single-material panel, which can directly determine whether it can meet the stress requirements according to its tensile strength. It has the advantages of being fast and convenient to avoid the trouble of finding the comprehensive mechanical parameters of the composite panel, and the calculation method has been verified by the software to verify that the calculation results are accurate and reliable. , a general method, and has a good promotion prospect.

本说明书中未作详细描述的内容属于本领域专业技术人员公知的现有技术。以上仅为本发明的实施例，但并不限制本发明的专利范围，尽管参照前述实施例对本发明进行了详细的说明，对于本领域的技术人员来而言，其依然可以对前述各具体实施方式所记载的技术方案进行修改，或者对其中部分技术特征进行等效替换。凡是利用本发明说明书及附图内容所做的等效结构，直接或间接运用在其他相关的技术领域，均同理在本发明专利保护范围之内。Contents not described in detail in this specification belong to the prior art known to those skilled in the art. The above are only the embodiments of the present invention, but do not limit the patent scope of the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still implement the foregoing specific implementations. Modifications are made to the technical solutions recorded in the method, or equivalent replacements are made to some of the technical features. Any equivalent structures made by using the contents of the description and the accompanying drawings of the present invention, which are directly or indirectly applied in other related technical fields, are all within the protection scope of the patent of the present 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
Figure FDA0003572143350000011
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
Figure FDA0003572143350000012
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
Figure FDA0003572143350000021
The equivalent section modulus of the lowest side plate is
Figure FDA0003572143350000022
The equivalent section modulus of the i-th plate is that of the plate on the upper side of the neutral axis
Figure FDA0003572143350000023
The lower side of the neutral axis of the plate is
Figure FDA0003572143350000024
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
Figure FDA0003572143350000025
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
Figure FDA0003572143350000026
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
Figure FDA0003572143350000027
Namely, it is
Figure FDA0003572143350000028
I e The moment of inertia is taken as the 1mm microsegment.
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CN111873558A (en) * 2020-06-19 2020-11-03 东华大学 Enhanced aramid honeycomb sandwich plate

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CN111027125A (en) * 2019-12-26 2020-04-17 东南大学 Honeycomb equivalent unit and parameter calculation method based on same
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