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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!

Really helpful tutorial. Thank you so much for sharing. It came out at the right time when I really needed it 🙏

Thanks for the set of lectures you have uploaded.

Hello sir in dynamic explicit can total energy become negetive ?

Great video about the link between Classical Laminate Theory and fem. A topic that too often is forgotten.

Hello Sir, if if one is doing the ABAQUS explicit dynamic crash analysis of composite tube (meso scale), is defining CZM for interlaminar failure necessary ?

Your video lectures are so much better than the professor I currently have! Thank you a ton!

Extremely useful video,thank you!!

useful informaation

positive zero crossings

allowable stress of fiber in helical layer and the hoop layer is the same ?

Hi. Can you please provide details as to why you do not consider Sxx(x=l,y)=0? and you are using the weak form?

Hi. can you help me. Consider a simply supported beam under uniform load transverse load on the tof the beam, why we do not put boundary conditions on Sxx (x=L, y)=0 and use the weak form?

Respected Professor thank you for uploading the video. I am working with a composite material and i need to calculate its mechanical properties but there are voids in the structure of composite you mentioned in the video that there is a method to take into account the voids present in the structure and that method is described in another video but after going through the videos i cant find that specific video can you please indicate where that video is. Thank you

PLEASE REPLY TO YOUR EMAIL

Thanks you pour explanation, please, What is the reference you use for your explanations (on micromechanics)

Hello sir, I am currently studying civil structural engineering and would like to potentially make the transition to aerospace in the future. If I were to go for a structural position, what gaps should I fill in? Is this transtion feasible?

thanks a lot for the vıdeo and the materıals.. I have been workıng on the composıtes nowadays.

Hi Vinay Sir, where can i get those two textbooks you have mentioned in the slides? also please guide about the website where you have posted the assignements.

Hello professor, what are the references used in the course?

@ 12:40 is that a force balance or a projection? How would sigma x' (pointed in the positive x' direction) be balanced by Px*cos(theta) and Py*sin(theta) if those decompositions are also pointed in the positive x' direction?

Thank you for this. I hope the rest of this playlist is similar to my Aerospace structures class as my professor is less than par.