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I'm looking into EASA 21J approval and found that EC 748/2012 is a little short on definitions. In particular, I'm looking for a clear definition of 'Design Activity'. It may well be buried in another related reg but I haven't yet found it if anyone knows and can direct me to it? Thanks in advance.

Norsok M-001 (Ed 5, Section 5.11.3) specifies that nickel grades 625, 59 & 686 are to be used in structural applications but that 625 can only be used at ambient temperatures. Table 10 goes on further to state that 30degC is the maximum seawater operating temperature. Elsewhere, the same Norosk...

Thanks Jay, I tried the extract as you suggested as I wanted to try and preserve the axes (since IGES doesn't preserve axes). As it turns out my FEA package doesn't understand CATIA parts anyway so IGES it is. Thanks again, Wade.

I'm trying to whip up a quick drawing to present it my stress report and am having trouble with stupid things like arrow head sizes. I'm not sure how to change them so I can actually see them. Also, is there any way to change the default arrow head sizes, dimension text sizes, etc so that I...

I have a complex solid but really just want the surfaces as I want to shell mesh it in Patran and don't really want the solid itself. Does anyone know how to extract the surfaces from a solid, I remember they used to call them 'faces' in CATIA V4 but not sure if that same function of extracting...

Hi Fernando, That's excellent information. Thanks for that. Wade.

I'm trying to determine whether a set of CATIA drawings are up to a general standard and wondered whether anyone out there had a general drawing checklist they could send to me or attach to this thread. Thanks.

I'm asking this question as an elementary user of FEM tools. I've been asked to calculate the tensile loads at some bolt positions based on the FEM nodal 'z' (out of plane) loads and I just want to make sure my interpretation of the FEM nodal loads is correct. Note that the nodes and bolt...

This may not be the correct place to post this but please feel free to direct me to a suitable resource. I've been given dimensions to some bolt locations in one axis system (lets call it axes 1) and I have only some of those bolt locations in a different axis system (lets call that axes 2). So...

Thanks for your reply but maybe I've asked my question in the wrong way. My actual panel thickness is indeed 56mm but I fear, with the way I've modeled it, i.e. with the facing sheet shell elements on the surface of the 40mm core and no offsets specified in the composite material section, that I...

Thanks for your response. I've just done a Show-Element-Coord System to check what you've said above and all elements (solid and shell) have the same normal direction (z) but as I said above, the x & y for the shells (which align with CID) = -x & -y for the hex's (not sure how to find out the...

I assume the shell element properties are applied at the centroid of the thickness of the material. I'm modeling a sandwich panel and what I've done is modelled the facing sheets on the surface of the core. But does this mean that half of the thickness of each facing sheet actually protrudes...

I'm creating a sandwich panel by using shells for the outer surface laminates and hex solid elements for the core. I'm creating the core elements by extruding the shell elements in the z direction. However when I do so, the resulting hex element coordinate systems are rotated by 180 degrees...

I've just found the answer on the net... So for anyone who's wondering, all you do is you go to; C:\MSC.Software\MSC.Patran\2004\shareware\msc\unsupported\utilities (that's if it's 2004 otherwise you path will be slightly different) and copy p3epilog.pcl from there into...

I have installed the utilities as per the instructions (refer to this thread: http://www.eng-tips.com/viewthread.cfm?qid=131288&page=1). However when I exit Patran and come back in again, I find that the Utilities disappear and I have to perform the same procedure again to get them back. Is...

Thanks for your reply. Basically I'm examining the effects on the stresses in a sandwich panel for different edge fixities. I'm using a/b=1 at the moment and defining all of my sandwich properties within the Patran laminate area (but that's not really part of the question). I'm aware in patran...

I'm fairly inexperienced at modelling in Patran and I'm trying to model a plate with fixities varying from fully fixed to simply support and everything in between. What I had though of doing is using spring elements between the plate and a fully fixed support then modifying the spring stiffness...

My question relates to the stepping down of material thickness on wing rib upper and lower flanges and I only wish I could draw a picture to make it clearer. I'm wanting to step down some flanges to save weight however this obviously causes stress concentrations. I've checked both the company...