iitdude
Aerospace
- Dec 22, 2011
- 5
Hi everyone,
I am currently using ANSYS-13 to study the post buckling analysis of stiffened panels. After performing non-linear analysis on the panel,the post processing results show the transverse normal strain in thickness direction is of the same order as the in plane strains. This should not be the case with the plate elements which are modelled using shell or solid element in ANSYS, because in ANSYS the fem formulation for both the elements is done using first order shear deformation theory. And according to this theory, the transverse normal strain must be zero or at least negligible. By the way i am using composite symmetric laminate and newton raphson algorithm to perform the non-linear analysis.
Can anybody explain what is the reason behind it?
Thanks in advance. reply awaiting.....
I am currently using ANSYS-13 to study the post buckling analysis of stiffened panels. After performing non-linear analysis on the panel,the post processing results show the transverse normal strain in thickness direction is of the same order as the in plane strains. This should not be the case with the plate elements which are modelled using shell or solid element in ANSYS, because in ANSYS the fem formulation for both the elements is done using first order shear deformation theory. And according to this theory, the transverse normal strain must be zero or at least negligible. By the way i am using composite symmetric laminate and newton raphson algorithm to perform the non-linear analysis.
Can anybody explain what is the reason behind it?
Thanks in advance. reply awaiting.....