VisibleConfusion
Aerospace
- Mar 15, 2019
- 7
Hi all,
I am new to this forum and have a question concerning composite failure analysis. I wasn't able to solve my problem with the existing threads, hence this new one.
I am currently working on a sandwich structure which is made from an aluminium honeycomb core and carbon fibre UD/epoxy faces. I have created different types of models to analyze deformation under load using Hypermesh (v2017.3) as a pre-processor, MSC Nastran (v2018.2) as a solver and HyperView (v2017.3) as a post-processor. This particular model of the sandwich is a rectangular 2d shell mesh, onto which I applied the PCOMP property. Within PCOMP I specified a 17-ply Laminate, where plies 1 to 8 and 10 to 16 are the face plies and ply 9 is the honeycomb core. I set Failure Theory (FT) to HOFF (Hoffmann) and also specified Bond Shear Strength (SB). The ply material is MAT8 (orthotropic), for the core I am using MAT2 (shell anisotropic). I specified all the required material Parameters (max. stresses etc).
Using Sol 101 I get my deformation and stress results "ply by ply", as desired. I am now trying to get an output of ply-by-ply failure indeces (FI) / strength ratios (SR), preferably the latter, but whichever is fine. I have set PARAMS,NOCOMPS,1 as others have pointed out on the forum. I am unable to locate any failure-related results in the .f06-file.
What am I missing?
Please note that I have only started working with Nastran and Hypermesh a month ago.
Kind regards
I am new to this forum and have a question concerning composite failure analysis. I wasn't able to solve my problem with the existing threads, hence this new one.
I am currently working on a sandwich structure which is made from an aluminium honeycomb core and carbon fibre UD/epoxy faces. I have created different types of models to analyze deformation under load using Hypermesh (v2017.3) as a pre-processor, MSC Nastran (v2018.2) as a solver and HyperView (v2017.3) as a post-processor. This particular model of the sandwich is a rectangular 2d shell mesh, onto which I applied the PCOMP property. Within PCOMP I specified a 17-ply Laminate, where plies 1 to 8 and 10 to 16 are the face plies and ply 9 is the honeycomb core. I set Failure Theory (FT) to HOFF (Hoffmann) and also specified Bond Shear Strength (SB). The ply material is MAT8 (orthotropic), for the core I am using MAT2 (shell anisotropic). I specified all the required material Parameters (max. stresses etc).
Using Sol 101 I get my deformation and stress results "ply by ply", as desired. I am now trying to get an output of ply-by-ply failure indeces (FI) / strength ratios (SR), preferably the latter, but whichever is fine. I have set PARAMS,NOCOMPS,1 as others have pointed out on the forum. I am unable to locate any failure-related results in the .f06-file.
What am I missing?
Please note that I have only started working with Nastran and Hypermesh a month ago.
Kind regards