Changes for page Cross laminated timber
Last modified by Iwona Budny Bjergø on 2022/01/12 12:20
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edited by Hamid Richard Allili
on 2019/11/25 15:13
on 2019/11/25 15:13
edited by Hamid Richard Allili
on 2019/11/25 15:13
on 2019/11/25 15:13
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... ... @@ 7,7 +7,6 @@ 7 7 8 8 The calculation of CLT panels is based on the laminated shell theory, which is a general way of calculating any kind of laminated shells, regardless on the material of the components. However, in the civil engineering practice the most popular application area is definitely the timber shells. Keep in mind this, in FD user interface the CL(T) feature strictly connects to timber panels, including the possibility for both analysis (internal forces/stresses) and design options. Moreover, to the make the best of the applied mechanical theory, general composite laminated shells are also implemented, with any kind of constituent material. As the design of these general composite shells are not supplemented by the standard, only analysis results are available of them. 9 9 10 (% class="wikigeneratedid" %) 11 11 = Definition on User interface = 12 12 13 13 ... ... @@ 27,7 +27,6 @@ 27 27 1. Cross laminated timber 28 28 1. General laminated composite 29 29 30  31 31 For the sake of uniformity, //Display stiffness// is available for all three kind of mechanical models. This matrix is calculated to the middle surface of the element (independently on the eccentricity of the General tab), it should be noted in the tooltip of this button. 32 32 33 33 [[image:1574680093243258.png]] ... ... @@ 63,7 +63,7 @@ 63 63 64 64 [[image:1574680319005894.png]] 65 65 66 The library elements are grouped by the producers, our aim is to implement many manufacturers’ product by default, it would mutually beneficial for both the producers and for FEMDesign. We can edit the new CLT library elements with the //New/ ////Modify// buttons:64 +The library elements are grouped by the producers, our aim is to implement many manufacturers’ product by default, it would mutually beneficial for both the producers and for FEMDesign. We can edit the new CLT library elements with the //New/Modify// buttons: 67 67 68 68 [[image:1574680418376297.png]] 69 69 ... ... @@ 88,3 +88,54 @@ 88 88 89 89 90 90 In this case, only mechanical properties are needed for a library element (as no design for them), and these values should be manually defined by the User (instead of selecting an existing material from the Concrete/Steel/Timber library). 89 + 90 += Analysis and results = 91 + 92 +Analysis of laminated type shell structures become available by a new mechanical model implemented into FEMDesign, based on the laminated shell theory. From civil engineering point of view, the most popular field of application is the cross laminated timber (CLT) panel, although the theory in itself is more general, it is applicable for any kind of laminated composite surface structure. As the main purpose of this feature is to calculate and design CLT panels, the currently existing Timber plate and Timber wall tools are supplemented with this calculation model. 93 + 94 +[[image:1574678804425887.png]] 95 + 96 +Although, the theory used for the calculation of displacements and stresses is general, the application data (e.g. deformation factor, service class, etc.) and design methods for CLT panels are very specific and standard dependent. In order to preserve the possibility of general application, two new options are added to the original mechanical model used for the calculation of timber shell structures (Orthotropic shell): Cross laminated timber and General laminated composite (GLC). 97 + 98 +For CLT panels, both analysis results (displacements and stresses) and design calculations are available, while for GLC panels only the first one is provided. These panel types are stored in different libraries, but their definition is very similar, we can define them layer by layer. In case of CLT, adding a new layer is possible by clicking on the material cell of the table, by this the original timber material library pops up, where we can select the constituent material of the current layer. After the selection, the program automatically fills all necessary data of the current layer, including mechanical properties (for analysis results) and limit stresses (for design calculations). 99 + 100 +[[image:1574689871786555.png]] 101 + 102 +It is very important that among the required layer data, there are some properties not specified by the Eurocode, these can be assumed based on the existing ones according to the following (in case the manufacturer does not specify different values for them): 103 + 104 +• G,,yz,, (G,,rolling,,) = G,,mean,, / 10 105 + 106 +• nu,,xy,, = 0.2 107 + 108 +• f,,Rk,, = f,,vk,, / 2 109 + 110 +• f,,xyk,, = f,,vk,, 111 + 112 +Of course, every value can be overwritten by demand. Besides the layers, the default deformation factors by service classes and stiffness reduction factors also need to be specified for a CLT library element. The new cross laminated timber library is filled up with the products of many famous manufacturers by default, new elements can be easily created based on them. The definition of GLC library elements is very similar, except that only the mechanical properties are necessary to define. For all the three mechanical type a display stiffness option is available to see the element stiffness matrix (refer to midplane) of the panels used in the calculations (and/or check its singularity), including the "B" submatrix responsible for the coupling effect. 113 + 114 +Models containing CLT/GLC panels offering both model space and detailed analysis results for load case, load combination, maximum of load combination, maximum of load groups, influence line and moving load maximum results. The first group contains the displacements, internal forces and stresses, where the former two are displayed in the same way as for the existing nonlaminated shells, while the stresses need some further options due to the laminated structure of these shells. A layer in which we would like to see the top/center/bottom stresses and a coordinate system also need to be selected the plot the wellknown stress result types. As the shell itself has a local system and all layers in the shell have a local system, the understanding of the stress components is not obvious, therefore the coordinate system is also an option it can be either "Shell local system" or "Layer local system". For example, the physical direction of a displayed Sigma x' stress varies according to the selected system, if shell and layer local system is not identical, which means the angle Theta defined in the library for the layer is not zero. 115 + 116 +[[image:1574690365292190.pngheight="397" width="922"]] 117 + 118 +It is worth to mention that in contrary with the nonlaminated shells, the transverse shear stresses (Tau y'z' and Tau x'z') can be also displayed at the top and bottom of layers besides the center, as in case of some intermediate layer they are not necessarily zero (for nonlaminated shells, due to the parabolic stress distribution the top and bottom values are always zero, only the center value can be selected from the shell stresses list). Due to the numerous options, finding maximum stresses by components on the shell can be quite time consuming, especially in case of the complex loading of the structure. In order to overcome this difficulty and make the maximum finding process way easier, besides the point based detailed result (e.g. for RC shells, Footfall calculation) a shell based option is also implemented. At the first option we can select an arbitrary point on the CLT/GLC panel, in the detailed result the geometry of the shell and the five stress components are displayed. As the whole section of the shell can be seen here, the coordinate system selector is supplemented with each layer's local system options. In case of maximum result (maximum of load combinations, etc.) plenty of maximum criteria available, which can be grouped by the following: 119 + 120 +• All components maximum (e.g. All components+): search for the combination(s) component by component which results the largest positive value of the stress component along all the layers at the selected point, on the stress figures the result of the combinations belonging to the components is displayed (note that there can be five different combination displayed in the detailed result) 121 + 122 +• All layer maximum by stress type (e.g. All layer, Sigma x+): search for the combination which results the largest positive x directional normal stress along all the layers at the selected point, on all the five stress figures the result of this combination is displayed 123 + 124 +• Layer maximum by stress type (e.g. 2. layer, Sigma x+): search for the combination which results the largest positive x directional normal stress in the second layer at the selected point, on all the five stress figures the result of this combination is displayed 125 + 126 +The second option to query a detailed result is the shell based option, where only a CLT/GLC panel need to be selected, without defining an exact point on it. 127 + 128 +PICTURE 129 + 130 +It is only available for maximum type results, the maximum criteria are the same as for the point based detailed result, except one significant difference: in this case the searching is not limited to a node, the program checks all node on the shell according to the selected criteria. For the first criteria group (All components maximum) the five stress component maximums may arise at five different nodes on the shell (also possibly from five different combinations), this result is excellent to see the overall maximum stresses on the shell considering simultaneously all nodes and all combinations. These nodes are displayed with position and node number on the geometry figure. In case of the second (All layer maximum by stress type) and third (Layer maximum by stress type) maximum criteria group the search focuses on one stress component, thus all stress figures display the result of the same node that provides the maximum for the selected component with simultaneous stress figures at this node for the other components. In the display options the scale/size of the figures and display/font of the values can be specified. 131 + 132 + 133 +The crosslaminated timber panels are supported with design calculations for ULS combinations and deflection check for serviceability limit states. The latter one can be performed on the analysis tab with the deflection check feature (further information can be found in the description of Shell deflection check). By setting different deformation factors in the application data of the panel for characteristic and quasipermanent combination types, both the instantaneous and longterm deflections can be checked properly according to the EC, respectively. In terms of the ultimate combinations, several checking criteria is available, some of them is optional (can be specified in the calculation parameter) as the EC itself does not contain them. Design check is available at Timber design tab, CLT panel design. 134 + 135 +[[image:1574691194768349.png]] 136 + 137 +The first group of design formulas are the wellknown stress checks from the Eurocode, extended to CLT panels: tension/compression and bending in both grain and perpendicular to grain direction, transverse shear stresses and rolling shear. The extension means that these checks are performed layer by layer (in the current layer's local system), at top and bottom or at parabola maximum in case of transverse shear stresses. The second group are three interaction formulas: shear interaction and tension/compression and shear. As these are not included in the EC5, in the calculation parameter of the CLT panel it can be specified that these checks should be considered during the design calculation or not. The third group are the buckling and torsional check. The shell buckling check of CLT panels are performed only for those buckling regions, which has nonzero buckling factor, also for those layers, which are less than 45° from the buckling direction. For the torsional check, typically applied for walls (in plane loaded structures), the "no glue at narrow sides" option must be checked in the application data. These methods are based on different standards and scientific papers, further information about the detailed checking process can be found in the theory manual of this feature: Theory of Laminated Composite Shells  CLT application. In the detailed result of the CLT panel the performed design calculations together with a geometry figure showing the critical nodes are displayed. 138 + 139 +