Wing Skin/Flat Panel Compression Limit

[@SoloRenegade]

Thank you for sharing your sources used as well. Helps when looking up further info.

[@thomassutrina7469]

Hi, I worked as a mechanical engineer for Sundstrand Aerospace (UTC). We had a vendor present the use of epoxy and rivet construction of school buses. The crash requirements changed without epoxy doubled the weight. Unacceptable so epoxy and riveting was tested, and no additional weight, thicker skin, was needed. The epoxy carried the shear load and the rivets prevented peel. You have the same structural problem.

[@SoloRenegade]

this is confusing to read and comprehend.

[@ailijic]

@@SoloRenegade it is not easy to read. I am pretty sure he is saying that the crash requirements of the school bus were way higher than the normal operating loads. To solve the problem they used epoxy and rivets instead of just rivets.

[@SoloRenegade]

@@ailijic I appreciate the effort, but it still makes no sense. " Unacceptable so epoxy and riveting was tested, and no additional weight, thicker skin, was needed." How can adding epoxy add no weight? yet they had to thicken the skin? that adds weight too. So they did more than just add epoxy, and they absolutely added weight. "The crash requirements changed without epoxy doubled the weight." what doubled in weight without epoxy? What changed? the requirements? the design? both? in what way did the requirements and/or design change to double the weight? This is barely "English", and even then makes no logical sense. It's missing half of the information necessary to comprehend it.

[@anthonyrstrawbridge]

The theory and testing ISA good start. Add life X 2 double the skin and rib thickness half the rivet spacing and use AN/Mil Spec rivets and hardware Chris has spoken.

[@michaelt5082]

really good info. I own the Hummel H5 and the Hummel Ultra Light. Both are plans and I have a lot of the metal out in the barn. I appreciate you talking about and using Morrys theories and stuff in this and the last video. I have no idea why some kind of "let's say glue" in between the rivets is not used. I am sure weight and a lot of other things are the reason. Just don't know why it's not considered?

[@SoloRenegade]

Perfect topic

[@gvc76]

Sorry dude, you jump back and forth between different orientations of the wing portion you’re examining, that it’s hard to follow. My advice: 1. Define the placement of the wing portion you’re examining relative to the entire wing. 2. Maintain the same orientation throughout your presentation. 3. If you need to jump to a different view to explain something, such as use a cross section rather than a top view, show them both, using acceptable drafting conventions, to help orient the viewer. 4. Establish early on the naming of the various dimensional features (i.e. length, width, height, thickness), and stick to them. 5. Be clear about the loading and load orientation relative to the portion you’re examining, and as before, stay consistent with the orientation of the load.

[@professorreedmatt6054]

Sir how do i calculate how many ribs are required for wing, my aircraft wing loading is 6 kg and total wing span is 1482 mm

[@Designer103]

It depends on now much load each rib can handle. You either select a rib spacing and then design the ribs to hand the loading. Or you determine how much load the rib can handle and then set the rib spacing to give the ribs the proper load.

[@ailijic]

You probably should watch Todd Coburn's videos, especially this one on effective sheet width and inter rivet bucking. kzbin.info/www/bejne/baKXqHafn5umbKM