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Aerodesign, Many thanks for the valuable information. It is nice to listen experiences of the colleagues, who followed the similar path before. I have been using PATRAN/NASTRAN for 11 years. To my opinion, PATRAN is a real disappointment story ! How a software that is paid thousands and...

Once more thank you Thomas. After a short search in internet, I have encountered a basis price of £5,000 (additional £1,000 is quoted as annual maintenance fee). It looks like there is a significant difference with PATRAN (I hear figures over £10,000 for PATRAN). Regards.

Dear Onda, It seems that Stezza's model is not a simply loaded simple beam model. Assume he has a skin stringer model or bar elements he mentioned are caps of a typical spar structure. In this case, bending moments at the same grid but belonging to the two adjacent elements would not be the...

Hi Thomas, Client does not require us any deliverable in .db format. MSC.NASTRAN is their standard solver. No discussion on it. I opened this thread in this forum on purpose. Because I am sick of MSC's marketing policy. Do you have any information about aproximate price of a FEMAP licence? (I...

Dear Forum Members, I am working on a project of establishing a firm, which will be an engineering service provider to a major aerospace company. PATRAN/NASTRAN couple is being used by this (customer) company. Therefore, at first glance,it seems that I have to consider purchasing these...

Stezza, As far as I know (I could be wrong), it is not possible with PATRAN what you want to do. It either shows average values at the center of the element or values at the nodes at two ends but again by averaging with values belonging to the common node of adjacent element. It does not...

RPstress, Sorry for the late response. Thank you very much for your explanations. I meant bearing-bypass interaction not bypass alone. Yes, I check shear-out & pull-thru as well. My main question was exactly about what you mentioned in your last sentence of your last quote. I agree with...

40818, Sorry but there is a misunderstanding. My question is about bearing-bypass interaction not pure bearing. Lateral restraint force (if it is not neglected) that you mention is considered as pure bearing load, according to my opinion. It has nothing to do with bypass because we have only...

Dear RPstress, I post an attachment, which is a pdf file showing a simple sketch. If there is only pressure load (no additional in-plane load), I think, it is not possible to talk about any bearing-bypass analysis. An I wrong? Best Regards...

Thanks for all the replies. My questions are arisen from some discussions done with colleagues from a major aerospace company. We performed bearing-bypass analyses by only considering in-plane loads at the edgeband. As quoted in the 2nd reply, we simply do not consider any bending. What they...

Dear All, I would like to ask your opinion about an issue for HC panels. We have a typical honeycomb panel with orthotropic face sheets . At edges of the panel there is an edge band region (monolithic). This HC panel is attached to a metallic backup structure from these edge band area with only...

Dear rb1957, I am not in global model business. But as far as I know,in the company that I work for, they model frames as BAR elements and skins as membrane elements and nodes are located at the outer loft. I did not see any shear cleat idealization in their global models. If I do the fuselage...

In global FEM, there is no shear cleat. Shear loads on them are calculated by simply taking the differences of normal forces (calculated from grid point force balance) at two ends of each BAR element idealizing the frame.

SWComposites - Question was whether there can be any tension load on the shear cleats due to internal pressure. In metallic fuselage structure I have never seen anybody who is trying to calculate such load acting on the cleats. Question was not about shear loads. Regards.

Thanks rb1957. Probably, since the magnitude is small, it is ignored for metallic designs. Therefore, in my short carrier, I have never seen that they have ever been taken into account. But in composite design, it seems, even this magnitude, that it can cause a problem because of pull-through...

My question is about loads acting on shear cleat attaching a typical fuselage frame to the skin. It is a Airbus design policy to use L- shape shear cleats to attach frames to the skin & stringers. In this case frames have no mouse-holes,where stringers pass through. Mouse-holes are on shear...

I have nothing to say against nastran (most of the time I work with global models and use linear static solution) but PATRAN is a disaster. In the office, it is one of the top three softwares, which are in our hate list.