carmenta
Aerospace
- Feb 3, 2015
- 3
Hello all,
I have a two cell wing box cell structure that has been idealized as concentrated areas for the flanges and stiffeners. The spar flanges and stiffeners are assumed to carry only axial loads and the skin and spar webs are assumed to take only the shear loads. My question is how would I model this in FEMAP to validate my numbers that I crunch out from the analytical solution. Currently I've modeled the problem in FEMAP using CSHEAR elements and CROD elements. The CROD elements are the for the concentrated areas and CSHEAR element for webs and flanges. The current configuration is each cell is 10 by 10 inches. I gave the model a depth of 20 inches. I have loaded the model at one of the concentrated areas (i.e CROD element nodes). I have attached the FEMAP model if anything is wondering of the configuration.
My question is whether I am modeling it the right way. I am unable to get the model to run with this configuration.
I have a two cell wing box cell structure that has been idealized as concentrated areas for the flanges and stiffeners. The spar flanges and stiffeners are assumed to carry only axial loads and the skin and spar webs are assumed to take only the shear loads. My question is how would I model this in FEMAP to validate my numbers that I crunch out from the analytical solution. Currently I've modeled the problem in FEMAP using CSHEAR elements and CROD elements. The CROD elements are the for the concentrated areas and CSHEAR element for webs and flanges. The current configuration is each cell is 10 by 10 inches. I gave the model a depth of 20 inches. I have loaded the model at one of the concentrated areas (i.e CROD element nodes). I have attached the FEMAP model if anything is wondering of the configuration.
My question is whether I am modeling it the right way. I am unable to get the model to run with this configuration.