UNSW - Aerospace Structures - Thin walled Beams (Shear)

[@jorialand]

Thank you for the lecture. It has served me for an Aerospace Structures exam!

[@stattics4449]

Thanks for the lecture,very interested

[@MegaMarkmonaghan]

Thank you for making this video, its cleared up a lot of confusion I had about finding shear flow for a closed section. However, I'm currently trying to solve a problem for a rectangular two cell closed section and am not sure how to go about finding q_so. Do you need to do each rectangle separately?

[@abheendrabandary5940]

sir in the diagram 23:37 the shear flow directions are also changed like instead of z it has to be s. is int it?

[@ayushgupta2158]

Awesome Lecture !!

[@obione6757]

simply beautiful

[@xfd]

Thank you so much...helped alot

[@mohiuddinsazzadmohiuddinsa1111]

is there any lecture on torsion?

[@suyogdani2702]

Thank you for a good lecture! :) Where is the next part ? (Because you say you'll give a work around about the integration.. which does seem seem easier..)

[@AerospaceStructures]

kzbin.info/www/bejne/rqTJpKh3mcySn7c

[@v_naymishra]

Sir, can u do a walkthrough of each chapter of Airframe Stress Analysis and Sizing by Michael Niu...?

[@pawankumar-ir1fd]

CANTILEVER BEAM, if the UDL is applied, so the SF will be different at different section of beam , in that case the shear flow will be same (magnitude)???? as if I take sections at different location. or this is for torsion only shear flow will be same at every location. PLEASE clear my doubt (2 hr. in video). your lectures are super excellent, Respect for you sir.

[@youxizhang1171]

this is helpful,thanks for uploading

[@7777Leander]

Super helpful! Thanks

[@purichmunlow8605]

One question regarding the shear distribution. Does the shear distribution change if one makes a cut at another region of the closed section?

[@AerospaceStructures]

Brilliant question. The total shear flow does not change, but the "basic" and "constant" parts do.

[@manaoharsam4211]

Video was great until 1.29 until the camera quit zooming in. Could not see formula . Have try to see if I can see on a bigger screen. I think you are doing a good job for beginner's. I am familiar with most till now. Yes you are teaching it very well no doubt. In one hr You taught a lot mainly because your slides were well prepared. I like the way you put the general bending moment equation and simplified it. These people on KZbin super lucky. I had to learn all this by myself. Teaching oneself is not that easy especially when you encounter very intense subjects.

[@shailendrasharma95]

Sir, which book should be perefer for Aircraft Structure.

[@AerospaceStructures]

In this course I primarily use T.H.G. Megson, Aircraft Structures for Engineering Students. For a more advanced option, Flabel is great.

[@aidealczar6075]

how do i find the position of maximum shear flow? just differentiate q23 = ....... + q12? (just differentiate the dotted part?)

[@anthonyesun]

Usually the max shear flow/stress is at the NA normal to the force causing a shear; NA positions are simply found using static moments and areas of the elementary pieces.

[@anthonyesun]

Probably it's good to know the fundamental approach, but in real engineering tasks to get a shear stress you simply divide force by area and multiply it by a cross-section shape factor (i.e. 3/2 - rectangle); or at least use a bit more generalized equation. Thank you anyways ;)

[@AerospaceStructures]

That approach works well for regular shapes but has a big drawback for aerospace structures. If you watch the next couple of videos, you'll see that we consider structures with discrete stiffeners and structures with multiple cells (very typical of the cross-section of wings). In both of these cases, you need the fundamental approach to make valid analyses.

[@georgen9755]

ceremic