if i want to move this load for diretion of moving car,how to define the move function? 4:16

I got an error message like this: "The following results file(s) could not be located: Linear_Buckling.fil". How can I solve this problem? Maybe the .fil has not generated in the right direction?

Hello sir ...I want to learn abaqus in fatigue crack....can u teach me

Hi, this equation has 2 variables like load is changing with height and time also? or just with time.

Thanks for sharing it 🙏

While calculating bending moment why the lever arm distance taken from centroidal axis? It should not be the distance from neutral axis?

hi sir,you're acsent is bit complicate for us.Could you explain more basicly or a bit slowly?? thanks..☺☺

Bro EAT all NPTEL

❤

Thanks for posting this. I'll have to look through some of those references. I've gone back and studied fracture mechanics recently and I'm interesting in how I can apply it to the design of damage tolerant composite structures. If you could recommend any resources on this topic I'd really appreciate it.

He keeps saying pre-cured, but does he mean pre-preg?

Thank you Master!

There is no need of giving inertia properties to the floor its analytical surface

Informative session

Thank you for the lecture, I wasn't sure if I drove equations in 3D correctly and it was super helpful.🙏🙏🙏

Hello Sir, Thank you for inviting Mr. Wei and For his very informative explanation..I would like to kindly ask if you have any content recommendations for doing a similar calculation for 3 phase composite RVE..

is it using Classical Laminate Theory or First Order Shear Difference theory for sandwich structure?

Finally, I will understand this topic! 😎

Thank you very much Dr. Goyal for sharing your knowledge, you make it easy to follow.

Very well presented

What does node file u do?

How do you decide the amount of vent area that facesheets have if you have closed off edges. For instance, we always use corefill on the edges, but it's unclear how many holes we should poke into the facesheet to vent. I have looked for guidance on that but it's hard to find.

Hi. Where is cohesive element used here?.....Cohesive surface is defined in the interaction property

thank you so much, this video saved me for my exam, excellent explanation

this is so cool. Thank you very much

I understand the shell model would be simpler and not able to provide thro-thickness information. So what is the key difference between using model 1 and model 2?

35:30

Very good explanation, thanks!

Note to self: complete

Thanks for this simplified explanation, greetings from Iraq 🇮🇶

great are slides available?

Thank you very much

Hello, i have been trying to copy paste this NACA 2412 file by using your Python script to ABAQUS but the sketch doesnt appaer. Can you help me please? from abaqus import * from abaqusConstants import * backwardCompatibility.setValues(includeDeprecated=True, reportDeprecated=False) import sketch import part myModel = mdb.Model(name='Airfoil Project') mySketch = myModel.ConstrainedSketch(name='Base Sketch', sheetSize=2) xydata = ( (1.0000, 0.0013), (0.9500, 0.0114), (0.9000, 0.0208), (0.8000, 0.0375), (0.7000, 0.0518), (0.6000, 0.0636), (0.5000, 0.0724), (0.4000, 0.0780), (0.3000, 0.0788), (0.2500, 0.0767), (0.2000, 0.0726), (0.1500, 0.0661), (0.1000, 0.0563), (0.0750, 0.0496), (0.0500, 0.0413), (0.0250, 0.0299), (0.0125, 0.0215), (0.0000, 0.0000), (0.0125, -0.0165), (0.0250, -0.0227), (0.0500, -0.0301), (0.0750, -0.0346), (0.1000, -0.0375), (0.1500, -0.0410), (0.2000, -0.0423), (0.2500, -0.0422), (0.3000, -0.0412), (0.4000, -0.0380), (0.5000, -0.0334), (0.6000, -0.0276), (0.7000, -0.0214), (0.8000, -0.0150), (0.9000, -0.0082), (0.9500, -0.0048), (1.0000, -0.0013) ) mySketch.Spline(points=xydata)

Amazing! Thank you for such good information!

Where can I find more information about Sean's research? I would love to ask him about his critical flaw size analysis.

Thank you so much sir for sharing these informative videos

Great video. This video is very useful. Thank you.

thanks for a good lesson!

can you please tell the criteria how you select the slice thickness (or node distances) and time step?

Amazing bro😊 Give more about adhesion and composite please

THANK YOU. Once again you've saved me. Tomorrow is my final in Aerospace Structures and your playlist is what has guided me through my course. I only need a 56% on the final to maintain an A in the class and I owe it to you. Thanks for the great semester professor!

thank you very much

Thank you!!

Very instructive video, thank you.

One of the greatest tutorials ever, thank you for sharing this video , great job

how the proccess to get T1-T9 sir🙏🏻

Professor, do you have any videos covering shear centers and/or idealized structures?

21:14 28 MPA*, not ksi

Great tutorial, quick question I have done the same procedure but I made my own model and followed your steps. but i see your origin has already been placed at 0,0,0. (Mine is somewhere else. How do I find out what the 2 origin points on my model are? currently the original has automatically been placed on the centre of the blade which is being assumed 0,0,0 and i cant generate result using that as 1st origin coordinate.)

Thank you for making these videos!