Greetings,
Its been a while since I used Ls-Dyna. Is anyone aware of a good source to get up to speed on running it, if so please provide the required details. The same thing goes for PAM-CRASH!
Thank you
Hassan Ziad Jishi
Aerospace Engineer (PhD)
issure the below command before solving,
/SOLU
EDRST,50
EDHTIME,500
EDOPT,ADD,,BOTH ! Write results files for both ANSYS and LS-DYNA postprocessors
EDENERGY,1,1,1,1
EDOUT,GLSTAT ! global statistics data
EDOUT,MATSUM ! material energy summary (on Part ID basis)
EDOUT,SPCFORC...
Dear all,
ANSYS APDL related question:
I am trying to automate the process of killing elements instead of applying each load step and killing elements separately. Below is a code that seems to be working, however, after each iteration, the .CM component file with the list of elements to be...
Hello,
I have obtained loads (shear force, bending moment, and axial load) acting on a beam. what guide should i use to size the beam that is in one case made out of a metallic material (alum) and another case made out of composite material (carbon epoxy).
Thank you
Hello,
I have modeled a composite cylinder with stringers and frames (the model is fixed at one end and subject to a downward force at the free end). I am trying to display shear stress in the skin; however, shear stress values (average of all layers) are almost zero. This does not make sense...
Thanks allot, i will investigate the reports. I never worked on fuselage structures before.
Regarding my model, it seems that adding the frames and stringers eliminated the problem of skin wrinkling. The next step will be adding floor beams to have a “realistic” model of a passenger door...
I am interested the effect of introducing passenger door cutout in both metallic and composite fuselage. I am starting off with the uncut metallic case first (only skin, no frames or stringers). I am going to analyze two separate cases, one being the bending moment shear force load and the...
The cylinder is meshed using Quad4 elements. 112 elements on the circumference and 80 along its length. One end is constraint in translation only <0,0,0> in the global coordinate system (coord 0).
The Hoop stress obtained matches closely the calculated value 77.408 N/mm^2.
I expected the...
I have created a thin walled cylinder in PATRAN as following:
Skin Thickness: 2.5 mm
Cylinder Height: 40000 mm
Cylinder Radius: 3280 mm
Material: Aluminum, Young's modulus 70000, v=0.3
Load: Uniform Distributed internal pressure=0.059 N/mm^2
After running the model, I noticed that the cylinder...
hello,
I am trying to add electrical cables to an aircraft model created on catia, all the parts are included. How do i go about routing cables and wires between equipment?
Thank you
Jishi
