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!
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.
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)
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.
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!
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.
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
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!
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
bro your doing great , hope you happiness and good luck
Great video. Keep them coming!
amazing video! please do more!
That is amazing thank you so much please we want more please 🙏 please 🙏 please more
this video has a lot of insight into aerospace engineering pliz pliz share more content
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!!!
Really appreciate the video!!!
Can you please share the CAD model, as it would be of great help?
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)
I wish there were more videos
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
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!
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.
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?