<
From version < 25.1 >
edited by Hamid Richard Allili
on 2019/11/26 14:30
To version < 26.1 >
edited by Hamid Richard Allili
on 2019/11/26 14:54
>
Change comment: There is no comment for this version

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88 88  
89 89  = Results =
90 90  
91 -Models containing CLT/GLC panels offer 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 non-laminated 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 well-known 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.
91 +==== Analysis ====
92 92  
93 +The following analysis results are available for CLT/GLC panels :
94 +- load case
95 +- load combination
96 +- maximum of load combination
97 +- maximum of load groups
98 +- influence line and moving load maximum.
99 +
100 +Displacements and internal forces are displayed in the same way as for the existing non-laminated shells.
101 +
102 +For displaying stresses some further options are needed due to the laminated structure of these shells:
103 +- a layer has to be selected
104 +- coordinate system has to chosen~://Shell local system// or  //Layer local system//
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 +
93 93  [[image:1574690365292-190.png||height="397" width="922"]]
94 94  
95 95  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:
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