great nicolas, i have over seen this ANSYS capability. Btw, it works only if you also know which elements should be died, so you need parameters too, isn't it?
cheers
DrBVVijay,
as i told you, that i have had the same question like yours : wether linear buckling solution exist or not, because i also had to optimize at that time a structure under pressure. I used at that time SQP algorithm and had also similar problem with you. Some times, the FEA-model could...
oic, you have applied "in plane" load to the elements, then the use of plate element is surely justified in this case. But it also means, that no stress stiffening effect will occure. To my know the stress stiffening takes effect only if the diplacement is normal to the stress...
toothroot,
Your problem can be completed two ways :
1. Using parametric options in ANSYS, of course also in PATRAN (but this rather complex), i.e. you model the changing portion of your structure parametrically. So you just need to change this parameter in every step. We have done similar job...
Hi all,
basically, i fully agree with dermotMonaghan. As addition to hits first paragraph : buckling will also occure in slender or thin-walled through "shear load", think at aircraft skin structure. Of course this is not the case for beam element, where buckling only through pressure...
Yes, first of all, it is not clear how you refine your elements (automatically with h-elements?). If not, then i agree with FeaGuru suggestion : refine the mesh locally (where the S.C.) is and see if it converges faster. Because only the S.C region is of interrest.
Regarding stress stiffening...
What vonlueke said is right, some FEA or structure people say, that beam element-formulation is exact, it means the FEA solution should match the theoretical solution. Therefore the solution of one beam is in general the same as the solution of, say, 10 beams or as stated by vonlueke : "you...
DrRaj, what you said is right, but this is valid only for 'normal' eigen modes, i.e without RIGID BODY MODES. I haven't read about no practical use of mode shapes of RIGID BODY MODES in aeroelastic : structural dynamic, flutter or dynamic responce. I have only heard from my "static"...
Hi, to my know, there is no practical use of frequencies and modal shapes of the 6 first rigid body modes of flying structures (airplane, spacecraft, ...). I mean for aeroelastic analysis, it is not needed. The only practical use of them, that i know, is for checking the quality of a static...
carbon carbon composites or CC (don't mistake it with CMC. that stands for Ceramic Matrix Composite) is carbon fiber embedded in carbon matrix or me can call it : Carbon Fiber Reinforced Carbon ;-). Unfortunately, i have loose my article about the process to make it, i am sorry not helping you...
there are some discussions about this phenomenon in some threads directed by our expert : bradh.
One can formulate as following : Shear locking, or parasitic shear, is caused by an inaccuracy in the displacement field of a linear quadrilateral or hexahedral element (Elements without mid-side...
Similar to version 5.5 and 5.7. There are always the some tutorials in this documentation, or do you mean other ANSYS turorial, then try to download it in the web.
Btw, you can find the ANYSY theoretical manual on http://www1.ansys.com/customer/content/documentation/60/ch01.html
good luck!
I have friend, that has modelled a piezo sensor integrated in an adaptiv structure with ANSYS, even he has optimized it with some iterations. If this match or similar to your requirement, then i will contact him to get the results or some hints to your problems. Of course, hints in this forum...
I have heard about this before, they said ANSYS V5R7 has problems with IGES export utility. So i have tried to export model in IGES with V5R8 and success. May be it was a simple model, but i would recommend you to migrate to higher release.
regards
