<
From version < 26.1 >
edited by Hamid Richard Allili
on 2019/11/26 14:54
To version < 27.1 >
edited by Hamid Richard Allili
on 2019/11/26 15:10
>
Change comment: There is no comment for this version

Summary

Details

Page properties
Content
... ... @@ -101,13 +101,19 @@
101 101  
102 102  For displaying stresses some further options are needed due to the laminated structure of these shells:
103 103  - a layer has to be selected
104 -- coordinate system has to chosen~://Shell local system// or  //Layer local system//
104 +- //Shell local system// or  //Layer local system //coordinate system has to be chosen.
105 105  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.
106 106  
107 107  [[image:1574690365292-190.png||height="397" width="922"]]
108 108  
109 -It is worth to mention that in contrary with the non-laminated 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 non-laminated 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:
109 +It is worth to mention that in contrary with the non-laminated 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 non-laminated 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).
110 110  
111 +====== //Stress detailed results// ======
112 +
113 +Two types of detailed result are available for stresses.
114 +
115 +//Point based stress detailed result~:// User 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:
116 +
111 111  • 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)
112 112  
113 113  • 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
... ... @@ -114,12 +114,13 @@
114 114  
115 115  • 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
116 116  
117 -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.
123 +//Shell based stress detailed result: //Due to the numerous options, finding maximum stresses by components on the shell can be quite time consuming, especially in case of complex loading of the structure. In order to overcome this difficulty and make the maximum finding process much easier a shell based option is also implemented, where User only has to select a shell.
118 118  
119 119  [[image:1574697194599-496.png]]
120 120  
121 121  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.
122 122  
129 +==== Design ====
123 123  
124 124  The cross-laminated 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 quasi-permanent combination types, both the instantaneous and long-term 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.
125 125  
Copyright 2020 StruSoft AB
FEM-Design Wiki