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I would pay to see you tackle some actual real world stress problems like bathtub fitting analysis, tension fittings, freebodies, lug analysis etc. Thanks.

Do you recommend using the same mesh for CQUAD and CSHEAR and just changing the element property assigned or does CSHEAR benefit from making a separate coarser mesh?

Had to chuckle a little bit at the shade thrown at the Boeing, Airbus, and NG. I’ve worked all thee and the first two definitely love the churn, especially AB. I worked sec 41 on the 747 for a while and they used bars for the frames in some of the older models. I remember actually going to an old library and digging up old microfiche and scanning through visually to find the correct element, output was a literal screen shot printed out like a xerox. The was in the early 2000s and they were still using that old way of doing things.😅

With a script you can extract gpforces from the f06 and plot shear and bending diagrams for rod/cshear, rod/cquad and cquad/cquad fem.

first

Thank you so much. I have gone over many videos on this topic and your explanation is so clear and easy to understand. Thank you once again for doing this!

Hello sir, on 23:36 you have the constants in the stiffness matrix 2nd row labled as C_21 C_22, however when you reduce the stiffness matrix at 34:23 you change the subscripts in the 2nd row to Q_12 Q_22. Why is that?

can we get the slides, they are actually pretty awesome.

Amazing ! thank you so much 😊

Did you wash your hands after this short?

This made me laugh, but it’s true. lol

Look what came up on my feed! Hi Todd from Boeing! Dan Ortiz says hi too.

wow, interesting message. Never though it that way. Thanks!

What’s the best way to prepare for entry level job technical interviews?

This is BS , ideas are a dime a dozen, NOBODY is looking for someone with an idea to give money to , You have banks and venture capitalists that are just scammers looking for someone to use and throw away. Whatever your idea is do it all your self with your own money and steer clear of the scammers.

Pansy is my new favorite word

Thank you Dr. Coburn!

Dear Mr. Cobum, I hope this message finds you well. I would like to express my gratitude for the explanations provided in your video on "Buckling for Flat Plates." The insights and clarity in your presentation were invaluable and greatly enhanced my understanding of the topic. Additionally, I would like to confirm if the reference book mentioned is indeed the Strength Handbook, Volume II. Thank you once again for your guidance and for sharing such useful resources.

Excellent lecture, thank you for posting Todd!

What is the app you are using?

Hello Todd, right here I would like to express my gratitude to you for preparing your latest handbooks. I am currently struggling with finding a job as my PhD thesis is at its end. I worked mostly with FEA simulations, thus I seek a job on that fiels. In my region it is mosty connected to aviation industry. I'm a complete newbie in this field, however learning from your book allowed me to surprise (positively) my future (i hope) technical leader at the interview. I have no guarantees that I will get a job under him, but I know that without your books, my interview results would me much worse. Keep going with your work here on YT, and in academia. Right now, student are thisty of knowledge directly from practitioners, not theoreticians. You have the ability to merge practice with theory in digestible way. I wish to be at your level (or even higher ;-) ) in the future Best regards Piotr from Poland

Kinda sounds like my gym teacher, I mean no disrespect

That verse is here…. Jeremiah 23:29 Is not my word like as a fire? saith the LORD; and like a hammer that breaketh the rock in pieces? Awesome lesson, T.C. 🤩👍👍

How do you qualify something as a not-so-long column?

Hats off to you guys - takes guts to start something like this with no knowledge...a lot would quit just due to the strain on your body - people just do not realise what proper labour does to the body .. ie. Cutting grinding drilling welding bending , loading Unless youve done it

🙂‍↕️

Hello Todd. Big fan of your work. I do have a content on AERO Structures. Your content is far ahead than my channel. I have recommended your Channel to my audience too.

Beautiful golden!!!

Thanks for all the helpful content Not all heroes wear capes!

@3:42, I believe there may be a typo on the slide there. For the A66 term (or the 3,3 term in the matrix shown), I believe the result should be 155.93 kips/in. I confirmed this result both through performing the math as shown on the slide and via my own calculation sheet. I think this is simply a transcription error from taking the results from your Matlab code to the slide.

thank you sir

Add some hands-on for how to make aircraft structures little aircraft. Thanks.

I am having a hard time understanding how the Y bar for the structure was 4.750 inches for the first example. if both the materials stack up to be 4 inches, how is the Y bar above the materials?

So its like Allah?

@20:20 Question on the sign convention of the allowable normal stresses F1 and F2. You mention that if f1 is compressive, then -F1c should be used for F1. However, why does the sign of F1, F2, etc matter? Wouldn't the square term cancel out the sign?

Finally someone that explains how to actuslly calculate it

Thank you

@30:42, I'm a bit confused at that chart. You state that at theta=90 degrees, a Ex/E2=0.1. But I would read that chart as showing that the values on the left axis apply to the ratios Ex/Ex, -nxy,x, and Gxy/G12. The values on the right axis only apply to vxy. It would seem very odd to have a graph that you switch the reference axis somewhere along the length of the curve. I would think you need to use the same axis for all three comparisons, theta=0,45, and 90. Thus, I would think Ex/E2 should equal one, not 0.1, when theta equals 90 degrees. Are we sure we're reading this chart correctly? I believe this may simply be a misreading of the graph. As a further confirmation, I took at a look at the reference where the plot originates, the Jones text. Take a look at problem set 2.6, specifically problem 2.6.7. The problem asks you to derive an equation for E1/Ex, but if you put in 90 degrees for the equation, you get that E1/Ex=E1/E2. Or simply, Ex=E2. And this does make intuitive sense. If you rotate a lamina 90 degrees, should apparent stiffness in the x direction not simply be equal to its stiffness in the 2 direction?

Another very thorough lecture. Really worth taking the time to go through. Thank you for uploading these. TH-cam is like trying to find gold in a landfill. You really have to dig to find high-quality expert content like this. But sometimes after wandering the warrens of TH-cam, you can find real gems like this, a literal rocket scientist providing free full-length lectures on composite laminate analysis. Thanks again for all your work.

Very Helpful! Planning to start drafting ahead of my professor so this is a big help! Thanks

At 34:04 In delta p equation it should be (x-x')/Iy right for that problem..

Great lecture, very well put together! Really thorough introduction to the material.

Thank you for sharing your knowledge 🙏🏼

this lectures are like Gem, Thankyou for your service..

Looks great! The link in description doesn't seem to work though, gives me a 404 not found. Also, are you offering a digital version?

Amazon warning: This item cannot be shipped to your selected delivery location. Please choose a different delivery location. Can you open to Turkiye for shipping. Other book (aerospace volume II) shipping to Turkiye but It doesnt. Please help!

Is it possible to explain bikkurim which means firstfruits according to my research. This video was amazing and eye opening.

Thank you.

Hi Todd, this is the great video to understand this bolt group analysis very quickly. The figure you are showing at 30:32 at the right bottom, vector for Y component for the left two bolts should be upward i think. Please correct me if am wrong. And one more doubt I have is, why do we use moment induced shear component as minus sign for Xstress and Plus sign for Ystress in the below two equation?

I've applied those simple bending moment models to pins and bolts many times in the past and they simply dont work when working to close stress limits. They give grossly over pessamistic results in relation to what actually happens in real cases, eg predicting failure when a connection with eccentricity has performed safely for many years.