Thanks all for the reply. I have quick question. why flat sandich panel does not show out of plane stress, if uniform pressure applied normal to flat surface?
I am analyzing a cowling of sandwich construction (carbon skins and honey comb core). It is idealized in FEA as shell (pcomp) mesh, presuressied by air loads. How should I evaluate the compressive strength of the core for the pressure loads, through the f06 element forces (Fx, FY, Fxy, Mx, My...
I am analyzing a cowling of sandwich construction (carbon skins and honey comb core). It is idealized in FEA as shell (pcomp) mesh, presuressied by air loads. How should I evlauate the compressive strength of the core for the pressure loads, through the f06 element forces (Fx, FY, Fxy, Mx, My...
I am looking for a good book that expalins clearly how to draw FBD. I need to revist my fundamental and would like to understand FBD, BM and SF diagrams for most common aerospace strucutres.
Thanks
Appreciate, if some one recomends good text editors (freeware) for Nastran deck. I had one good flexible text editor, that highlights all nastran keywords and wors well with huge text files. But I forget the name now. If any one has one, please recommed me.
I am a hypermesh user for more than 8 years in auto industry. Now I intend to change job in aerospace industry, so I am trying to learn Patran. It makes me so sick to learn Patran. Why do all aerospace companies stick to Patran? Howmany of them started considering other tools like Hypermesh for...
I could spend some time to dig in this forum to model the honeycomb sandwitch panel. Gbor and swcomposites have posted very good informations. Therefore, I decided to use pcomp card with 3 layers (skin,core,skin)in the shell mesh. I use Mat 8 card for core and provide G13 and G23 values as...
When I post process the result of an analysis with composite layered elements (PCOMP elements in NASTRAN), I could see the solver outputs von-mises stresses for PCOMP elements, apart from stresses in each layer of the composite.
I wonder, how it calculates von-mises stress of a composite pcomp...
I am trying to get material constants for a carbon fiber prepreg to be used in my PCOMP card.
The prepreg is a unitape(BMS 8 276 qualified) Toray 3900 series material made from T-800H carbon fiber. It is a 350F cure epoxy system.
I got very few properties from Toray website. Then I used...
I want to analyze a carbon fiber structure made from 350cure graphite/epoxy unitape. The geometry is a very simple T shape bracket. It is a simple square flange and a vertical rib on it.
Here is the lay-up. The carbon fiber lay-up is made, such that two L shape brackets are co-cured along the...
I am planning to do bearing hole strength of carbon fiber laminate coupons as per ASTM D5961.
The standard recomends to use coupons having 0.25 inch hole and same diameter pin, with Width/Dia ratio 6 and edge/dia ratio 3.
Now my big doubt is that, for a given thickness of a laminate, Is the...
Swcomposites,
Further on this topic, I doubt my failure strain values used in quasi isotropic laminate. These values are important in determination of failure indeses based on max.strain failure theory. We know the XT,YT, Xc,YC and Sxy of a single lamina. The compro program does not report...
I am studying carbon fiber laminate for structural loads thro FEA. I use hypermesh/optistruct (same as Nastran keyword format) to analyze the FE models. My model contains 64 lamina with repeating material directions. (The laminate has 8 quasi-isotropic lamina assemblies. Each quasi-isotropic...
