Buckling of Aircraft Panels with Integral Stiffners
Buckling of Aircraft Panels with Integral Stiffners
(OP)
Hello everyone!
Just a question I have,
Obviously the aircraft industry is now satrting to look into the use of intergrally stiffend panels instead of the traditional riveted assembly. This provides obviously cost and weight savings. Perfect!!
But what I am wondering is, what effect (negative, positive or negligible) does the introduction of integral stiffeners have on the buckling performance(particualry intial buckling under compressive loading)of the structure?
Thank you
Just a question I have,
Obviously the aircraft industry is now satrting to look into the use of intergrally stiffend panels instead of the traditional riveted assembly. This provides obviously cost and weight savings. Perfect!!
But what I am wondering is, what effect (negative, positive or negligible) does the introduction of integral stiffeners have on the buckling performance(particualry intial buckling under compressive loading)of the structure?
Thank you





RE: Buckling of Aircraft Panels with Integral Stiffners
1) the same area,
2) the same load,
3) the same stiffener pitch,
...
basically, you get the panel you design. will an integrally stiffened panel be lighter for the same load ? probably.
remember, however, you can't mix materials (like you would like a lower wing plank, conventionally 2024 skins and 7075 stringers), and the residual strength of an integrally stiffened panel is lower than a rivetted panel.
RE: Buckling of Aircraft Panels with Integral Stiffners