davide123
Guest
Good evening to all of you,
I have been tribulating with the modeling of sandwich panels for an ultralight aircraft. for now I apply the panels only to the seat (in figure) to see how it reacts; the thickness of the same is 40mm, as evidenced in the next figure; I had decided to proceed with the core the nomex (the properties of which are in the image namex) and with the carbon plates ortotropic (always in figure the properties). I now proceed with the constitution of the composite as in the image "laminated"; the elements are cquad4 in 2d; now when I go to the properties, I choose shell, 2d, but then in the input properties, how thick do I put? I tried to put 20mm, but the weight becomes 40 kg almost, when I need only 15. Can someone help me? Thank you in advance,
Mar
I have been tribulating with the modeling of sandwich panels for an ultralight aircraft. for now I apply the panels only to the seat (in figure) to see how it reacts; the thickness of the same is 40mm, as evidenced in the next figure; I had decided to proceed with the core the nomex (the properties of which are in the image namex) and with the carbon plates ortotropic (always in figure the properties). I now proceed with the constitution of the composite as in the image "laminated"; the elements are cquad4 in 2d; now when I go to the properties, I choose shell, 2d, but then in the input properties, how thick do I put? I tried to put 20mm, but the weight becomes 40 kg almost, when I need only 15. Can someone help me? Thank you in advance,
Mar
