Hey! I know this video's been out a while but I wanted to say that your explanation of engineering first principles as well as basic wing structures is very well articulated and I enjoyed watching it even if it was just review from my perspective. That part of video is definitely a goldmine of the basics for any non-engineers or those without experience with aircraft.
Thank you so much for sharing your knowledge. The tips, tricks, shortcuts and best practices you show us here are really appreciated and I am sure will be referenced by others for many years. Looking forward to your next video. I watched the entire tutorial and keen on working again with Femap. Last time I tried it was when it was embedded in MSC Nastran for Windows (~1998). Would love if you could share this 3D geometry in a link. If possible, I would like to propose a further tutorial using this model, since you have already set it up: 1. Include contacts between skin and ribs, stringers (even if it's just glued i.e. linear contact) 2. Modal analysis 3. Inset any solid model bracket at the root of the wing and connect shell elements at the root to some solid elements 4. Increase the load until some section of the wing's material just reaches yield and do a non-linear analysis Always appreciated and thankful.
I'm building a Vans RV-10 and the insight into the how and why these structures are interlinked and the stresses measured was fascinating. Thanks for sharing this!
Thanks for a great video! I’ll echo others about the very slow start, and a bit of laborious follow along (once I see how to do one rivet, I can probably do most of them ;-). What this has done is to really turn me off the idea of doing any FEM for my wing: THIS IS A PAIN IN THE ASS! First, this software is not intuitive or user friendly. I’ve used software like this, and you really need to do it for a living to be able to do it right and do it efficiently. So other than maybe the initial design work, this analysis is best hired out. But that was a very valuable lesson to learn. My follow in question is if there is not some other FEM that is easier to use? Looks like a good potential area for applying AI.
What will happen if you just defined the thickness before exporting into FEMAP? I'm using solidworks to model my wing. Love the video! This is helping me with my senior design project so far.
Thank you for making this video. Can this program model anisotropic materials such as a solid spruce spar or three layer 1/16" mahogany plywood at 45 degrees to the span for skins? And how are glued joints modeled? My spar is solid douglas fir; all ribs are truss type bent 1/4 x 1/2" douglas fir, skins are 0.105" mahogany on the 45, epoxied down to ribs on 6" centers. Typical strut braced high wing monoplane. Trying to model the contribution of the skin as it buckles is challenging; the wings are already fabricated and I need to know whether to stiffen the skins a bit with some uni carbon on the outside. Appreciate your effort presenting this level of detail. It is fantastic.
Hey. To model your general fasteners as CBUSH elements, my mentor was telling me he uses DOF springs, with Huth or Douglass stiffnesses for all the directions. Your Spring/Damper element type in this version of FEMAP looks similar to what menu I normally look at.. What’s the difference? Cheers, Great video!
hello!Really liked your video,everything was detailed and possible to understand.Is there a possibity to try to wrk with your cae model by myself?Will be really glad if you may send the model)
First of all thank you for this resource but why don't you separate the face into upper, lower and leading face as in real situation? Is there any advantage or disadvantage?
anyone watching this video probably knows how a stressed skin aircraft wing is built, please dont waste time explaining that get on the the stress analysis please.
This is completely untrue. I am building a stressed skin wing entirely out of wood. There are no fasteners and the materials are anisotropic. The construction methods are obviously critical in determining how the components are fastened and how that is modeled in FEMAP
Hey! I know this video's been out a while but I wanted to say that your explanation of engineering first principles as well as basic wing structures is very well articulated and I enjoyed watching it even if it was just review from my perspective. That part of video is definitely a goldmine of the basics for any non-engineers or those without experience with aircraft.
Thank you so much for sharing your knowledge.
The tips, tricks, shortcuts and best practices you show us here are really appreciated and I am sure will be referenced by others for many years.
Looking forward to your next video. I watched the entire tutorial and keen on working again with Femap. Last time I tried it was when it was embedded in MSC Nastran for Windows (~1998). Would love if you could share this 3D geometry in a link.
If possible, I would like to propose a further tutorial using this model, since you have already set it up:
1. Include contacts between skin and ribs, stringers (even if it's just glued i.e. linear contact)
2. Modal analysis
3. Inset any solid model bracket at the root of the wing and connect shell elements at the root to some solid elements
4. Increase the load until some section of the wing's material just reaches yield and do a non-linear analysis
Always appreciated and thankful.
Thank you for the comment! I can definitely do a video on those topics in the future
I'm building a Vans RV-10 and the insight into the how and why these structures are interlinked and the stresses measured was fascinating. Thanks for sharing this!
bro your doing great , hope you happiness and good luck
Great video. Keep them coming!
That is amazing thank you so much please we want more please 🙏 please 🙏 please more
Thanks for a great video! I’ll echo others about the very slow start, and a bit of laborious follow along (once I see how to do one rivet, I can probably do most of them ;-). What this has done is to really turn me off the idea of doing any FEM for my wing: THIS IS A PAIN IN THE ASS! First, this software is not intuitive or user friendly. I’ve used software like this, and you really need to do it for a living to be able to do it right and do it efficiently. So other than maybe the initial design work, this analysis is best hired out. But that was a very valuable lesson to learn. My follow in question is if there is not some other FEM that is easier to use? Looks like a good potential area for applying AI.
amazing video! please do more!
this video has a lot of insight into aerospace engineering pliz pliz share more content
Really appreciate the video!!!
Can you please share the CAD model, as it would be of great help?
It would be nice if one could color the rivets based on their stressforces. If can export with xyz, could pull into Matlab and plot it.
This is great! Are you planning on doing more of these videos? I would love to see more. Composites aircraft videos would be cool.
amazing video!!!
I wish there were more videos
Why would you not attach the ribs to the stringers? Seems that would increase strength and stiffness.
What will happen if you just defined the thickness before exporting into FEMAP? I'm using solidworks to model my wing. Love the video! This is helping me with my senior design project so far.
that is also my question but i did it with surface in solidworks and it works
Thank you for making this video. Can this program model anisotropic materials such as a solid spruce spar or three layer 1/16" mahogany plywood at 45 degrees to the span for skins? And how are glued joints modeled? My spar is solid douglas fir; all ribs are truss type bent 1/4 x 1/2" douglas fir, skins are 0.105" mahogany on the 45, epoxied down to ribs on 6" centers. Typical strut braced high wing monoplane. Trying to model the contribution of the skin as it buckles is challenging; the wings are already fabricated and I need to know whether to stiffen the skins a bit with some uni carbon on the outside. Appreciate your effort presenting this level of detail. It is fantastic.
Hey.
To model your general fasteners as CBUSH elements, my mentor was telling me he uses DOF springs, with Huth or Douglass stiffnesses for all the directions. Your Spring/Damper element type in this version of FEMAP looks similar to what menu I normally look at..
What’s the difference?
Cheers,
Great video!
hello!Really liked your video,everything was detailed and possible to understand.Is there a possibity to try to wrk with your cae model by myself?Will be really glad if you may send the model)
First of all thank you for this resource but why don't you separate the face into upper, lower and leading face as in real situation? Is there any advantage or disadvantage?
Fucking Legendary!
anyone watching this video probably knows how a stressed skin aircraft wing is built, please dont waste time explaining that get on the the stress analysis please.
I'm the exception. I'm building an Vans RV-10 and this provides so much insight into why these aircraft are built the way they are.
This is completely untrue. I am building a stressed skin wing entirely out of wood. There are no fasteners and the materials are anisotropic. The construction methods are obviously critical in determining how the components are fastened and how that is modeled in FEMAP
Thank you for sharing the video!!
I run FEMAP as well, anything you need you can contact me, a pleassure to help, thanks!.
Best regards,
Blas.
Hello my friend,
I have a very similar project and I really need your help. You have done a great job in this video. Please contact me.
hello! Is model found?
@@1billionidea Hello. What do you mean?