hi everyone,
I carried out a linear buckling analysis of a skin panel using nastran solver 105. The loads were applied as enforced displacement form a global model. surprisingly first mode buckling factor was 0.06365. Iam quite sure that the panel will not buckle at the applied load times the...
I do not know whether I am posting my concerns in the right forum or not. I am a aircraft structural engineer. I always encounter new or updated loads on wings from aerodynamics.I generally use excel and convert these loads into FE nodal loads.Now I want to write a generalised program for nodal...
Dear all,
I do have a general model of nose box. The spar web has a cutout. But FE model does not have it. The web has around 18 CSHELL elements between two stiffeners. The shear flow values vary from 30 N/mm to 150 N/mm. My doubt: Should I take max shear flow or average shear flow or…(no idea)...
Dear all,
conversion of Pressure distribution to FE nodal loads is a huge work and to do it manually is time consuming ,if it involves lot number of load cases. Is there any program available to convert pressure distribution to FE nodal loads.Kindly can anyone refer. Thank you in advance.
shearlag
Dear all,
Is the ratio (longitudinal extension strain)/(transverse contraction strain) is a very useful criteria for choosing high strength Uni Directional carbon Tapes (like T800 or VKU-27 or M65) ?. If so , why ?
thanks in advance
with regards
shearlag
Dear all,
Can any of you kindly help me in successfully executing a Nastran program for sandwich panel?
Since the problem is of sandwich wing skin, the upper and lower wing skin is represented using CQUAD4 using SHELL topology. The top facing and the bottom facing ( 15 layup of 0.13 mm each) is...
Dear Readers,
If chordwise & spanwise CP distribution is known, nodal load can be evaluated on each node on the Fe model. If forces & moments are known at few locations (say 15 locations) on wing surface, what is proper way to distribute the load so that shear force, bending moment & torque...
Dear all,
Is it possible to obtain grid point force summation about a perticular node in local coordinate so as to get all the six quantities (3 forces & 3 moments),so that any perticular section can be checked for strength using classical methods.I tried in PAtran & got all zeros similar to...
Dear all ,
Can anyone tell me how to execute many *.bdf,s files using one NASTRAN command.I do have 800 *.bdf files for a perticular set of load cases.As a usual method, one can be executed at a time. Or create a batch file & execute all, for which all the input file name needs to be keyed...
Dear all,
Can anybody suggest me as how to execute many nastran input files (*.bdf) with a single command.
For a perticular load case i have created 358 *.bdf files. Usual way is to execute one after another. or create a batch file and execute it.But for a batch file, one needs to key in all...
Dear all,
Can any of you help me to interpret the results of material non linearity analysis run on NASTRAN SOL 106.Material is AMS 4010 and properties are UTS:510 MPa, YEILD:450 MPa & ductility is 9%.As explained in nastran, i have input a stress-strain curve.My first point is (0,0) & second...
Dear all,
Iam working on in-flight strain analysis and for some reasons unable to match (not even reasonably) the in-flight strain recorded by the strain gauges. Assuming that the strain gauges are bonded properly and the inflight strain data are correct.
I have got few doubts like…
At maximum...
Dear all,
Iam new to this forum.Iam basically a stress engineer.
We are into designing a T-tail for a military transport aircraft
Please fellow members, can anyone tell me any books, technical papers, journals or any manuals to refer to start with.
I only know that design requirements are...
