RPstress
You can apply loads to most of the ones I mentioned in my initial post. MDSolids is quite nice for that purpose. My only gripe with MDSolids is that it's not flexible enough from modeling of cross-sections point of view as you are restricted to a finite set of shapes.
Cheers! :-)
Sparweb
Thx 4 ur feedback.
My problem is that I try to stay away from CAD software :o)
At Boeing I got spoiled with SA and found it very! quick and easy to drive and run - not only for section properties but also for local compressive instability (crippling) checks.
I was hoping...
mcclain
BDM 6040 is not publicly available as it is propietary data. However, sometimes this type of data sometimes falls of the back of trucks and job-shoppers are quickly to pick them up - solely in the interest of keeping our roads clean of ocurse. ;-)
jeaz123
Thanks for your feedback.
I agree that the 0.9 factor is an easy way of developing consistency within Boeing - a way to account not only for real behaviour but also to ensure Northrop's assumptions (when they did the 747 fuselage stresss analysis) are maintained.
The problem I'm...
epeus,
thanks for your feedback. I agree MDSolids is quite a useful tool. I will give the one swearingen recommended a spin. I wonder if there's anything out there that you can easily build complex shapes out of basic "building blocks". Will let you know if I find something.
rb1957
N/P regarding your dreaming about lugs ;-)
regarging your comment "i'd have thought that fatigue allowables would be critical, so there'd be a +ve static margin for the ultimate case": IMO it would depend as to the what the ultimate design condition is and the specifics of the joint...
Rpstress
thanks for the reference to the BDM - I will look into it this morning.
It appears that Boeing, Northrop, and Hawker Sidley's approach show a common thread: there is an additional knockdown from what a strict net area calculation would predict a fastened joint to be able to carry...
Hi!
I have been looking for a simple software that would allow me to calculate Section Properties (Ix, Ixy, Area, etc) for a wide variety of cross sections.
At Boeing we had a program called Section Analysis which was very good for stress analysts. You could choose from "primitive building...
ieaz123 - thanks for your feedback! Could you please tell me the BDM number so I may try to locate the limitations within the decsribed technique? Thanks again!
RPstress:
Thanks for your very detailed reply. A few comments:
You state: “The section has graphs of sigma_D/W vs. the reduction factor on the UTS. (sigma_D is the sum of all the diameters of the holes across the specimen - some specimens were single holes and some were multiple holes in a...
rb1957
Thanks for your reply! I will try to clarify my previous post by commenting to your reply:
"the 0.9 factor (tho' i'd dispute calling this a stress concentration factor ... 1/.9 might be)" - I agree this is a so-so term. The reason Boeing used the term "stress concentration factor" is...
Hi!
During my 12 yrs @ Boeing (747/767 Stress) we routinely used the following formula to calculate the net area capability of structure having fastener details:
Allowable Load = 0.9 X Ftu X Anet
From Boeing's internal course No. V4011.6 titled "Detail Design and Analysis"- taught by Gus...
Hi whalesA3D!
Thanks for your input. I haven't worked @ Douglas; therefore, the info I quoted was hear-say. I appologize if inacurate[upsidedown] .
I worked @ Boeing from 1984-1996 mostly as a 747 Stress Analyst. Throughout this period I am certain that Boeing's Definition of "Edge Margin"...
