Thanks rb1957. My approach is using the Conservation of Energy Bernoulli equation and also the low of conservation of mass. Once we have decompression, the pressure from one side of the bulkhead will start droping with curtain rate, but the pressure from the other part of the bulkhead will start...
Hi,
I am trying to find what would be the load on Aircraft Bulkhead during A/C decompression. It looks like a fluid mechanics problem. Any suggestions will be highly appreciated.
Steven, futhermore to your reply, nz of 2.5 is a conservative, since is a denominator in an equation for sigma 1g max-longitudinal stress. So, the bigger nz, the less sigma 1g stress and therefore less equivalent longitudinal operating stress, which affects big times the final AFGROW results as...
Thank you Steven for your comments, I think you've put some nice thoughts which can be considered. We went to external doubler, since we are accomodating two small antennas in two adjacent pockets, top fuselage crown and that was more practical instl. Thanks again for your comments,
cheers,
...yes, I am using Chicago DTA for antenna instl, and as you can know long. stress increase linearly up to the front spar and stys const. after that. Conservatively for nz you have to use 2.5, however, if you can validate this number from OEM CFR 25.337(b) says that you can go from 2.5 till 3.8...
Thank you rb1957 for your espond. Yes I have a doubler (external one, under the antenna) and in my case, critical is not hoop, but longitudinal stress, since the antenna location is very close to the front wing spar STA location, top crown skin fuselage. And that is waht is nocking me down my...
I was doing DTA analysis on antenna installation on an A/C and have used conservatively nx = 2.5 (max design limil load factor). if anyone was involved in that type of calculations, I would appreciate any hints, how I can icrease that number (as per CFR 25.337(b) nz is between 2.5 and 3.8), so...
