Search results for query: *

Looks like lath and plaster were on the walls, so likely built long ago.

You better be certain that the welding heat does not destroy the core to facesheet bond. Also, show a sketch of your part.

vinyl siding is not a structural material. Ignore it.

If he works for the same company / agency as you, why don’t you ask your manager this question? Seems like an internal political thing.

wdr36, If you think the job market is bad now, you should have seen it in the early ‘80s. Anyway, please answer some questions: - where are you located? - what degree do you have? level and field? - what type of companies have you applied to? In what locations? - have you gotten any interviews...

Run a fatigue durability test with and without a sleeve, and let real data guide you. Do you really want to put a durability problem into service?

External is way easier to fabricate and inspect in service. Note, design of fuse pins is not easy. And you cannot rely solely on FEA. You must test them.

Its all about durability/ wear under fatigue loads. Hard to analyze. Hence why companies have design rules and guildelines. Every aerospace fitting that I have seen that has a pin joint for moveable attachments has bushings in every hole. Typically steel or nickel-bronze. Those bushings...

the shear flows in the bays will be the same IF there is no change in thickness, depth, width, material in the skins and spars down the length.

Yes, the box will buckle and/or collapse without the ribs. Do you think aircraft designers have added ribs to wing boxes for 100+ years for no reason?

what preprocessing code are you using? suggest deleting this post and reposting in the specific forum for the code. and the mesh at the points in going to be a problem.

Sounds like a homework problem. What is the trouble you are having? Post your calculations in detail.

no, you do not fix all translations in a pinned end. you only fix the lateral translations. you do not fix the axial direction translation at both ends, only at the end that is not loaded.

using scholar.google.com brings up a number of similar papers.

Do it in Excel. Output all of the node definitions - ids and coordinates Sort by coordinate locations. Coincident nodes should be adjacent. Create CBUSH cards in Excel using character strings. Out CBUSH cards and read into Hypermesh.

Make a FEM of a flat plate size of Bay 1+2 and do a study of buckling loads: Uniform load. Different ratios of Bay 1 to Bay 2 loads.

Go into management.

I don’t see how averaging the loads, even if justified which I don’t think it can be, could possibly show the larger panel good. The buckling loads, both in shear and compression, will be lower than that of the individual smaller panels. For more detailed help, provide The buckling loads of...

Have you asked the supplier for their advice? Did you specify the details of the aging process or did the supplier select the process?

If you are modelling the bolts with solid elements, well, to be frank, that is gross overkill and its not going to be accurate anyway. All it does is make for a very complicated model and will generate lot and lots of output for which you won't know what to do with. What are you going to do...