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Burner2k i have not worked on composites, so i don't have any documents related to that. Fatigue and DT, is there any particular document or component you are looking for. I will upload one document that i used in only one project that i have worked on...

Hi RB1957, thanks for responding and answering my questions. I am afraid i have understood only part of your reply and have further questions on some of your explanation. I will start with what is have understood, based on your reply: 1) Because of the greater depth in fuselage compared to...

Burner2k, is there any particular topic you have in mind? Post it here, and if i have the document then i will share it here.

Hi all, Please find the link for APA115v3 document. http://files.engineering.com/getfile.aspx?folder=4306e038-13d4-47f2-a68b-84ec56d3a449&file=apa115_vol_3.pdf

Hi Burner2k, Please find the link to SOR51. Now a question for all the gurus, there is a graph on pdf page number 28. This is used to calculate permanent deformation at limit load and panel failure at ultimate load (This in turn is combined with stiffener stresses, by a equation similar to...

Hi RB, This is with respect to your post on 16 Nov 15 19:34. Is there any difference to modelling of skin stringer in fuselage and wing skin, as you repeatedly mention the skin offset. Is it because of thicker wing skin compared to fuselage skin?

If you can get APA115v3 manual then that covers all the topics that you have mentioned. APA115 is an Airbus collection program and v3 manual is a total description of it. This program is specifically mentioned for shear panel analysis. It is basically a implementation of SOR51. If anyone needs...