Wing Skin Loading

[bigred89]

I'm working on a wing skin problem that's giving me trouble:

The wing skin is made of aluminum alloy 2024-T3 and is subjected to a distributed load due to aerodynamic pressure during flight. The skin panel is rectangular, measuring 2 meters long by 1 meter wide, with a thickness of 3 millimeters. The panel is riveted to the wing ribs and spars along its edges.
Determine:

1. The maximum stress in the wing skin panel under a given loading condition.
2. The deflection at the center of the panel.
3. The margin of safety against yielding and buckling.

Given:

• Material: Aluminum alloy 2024-T3
  • Young's modulus (E): 73.1 GPa
  • Poisson's ratio (ν): 0.33
  • Yield strength (σ_y): 345 MPa
• Panel dimensions:
  • Length (a): 2 m
  • Width (b): 1 m
  • Thickness (t): 3 mm
• Loading condition:
  • Distributed load (q): 10 kPa (representing aerodynamic pressure)

 

[SWComposites]

Sounds like a homework problem.

What is the trouble you are having? Post your calculations in detail.

 

[rb1957]

Yeah, this is very much a school question ... who'd make a wing skin panel 1m wide without stringers ? who'd make a wingskin 2m * 1m by 3mm (1/8") thk ??
and as such should be in the student forum.

You'll have to make a 'boat-load" of assumptions ...
simply supported edges,
pressure only, no bending loads (which are there, 'cept if you say they aren't !?)

look up Roark for the solution ...

MS for buckling ... that'll be an interesting calc !??

 

[dcascap]

This is a homework question, please post in student forum.
I second rb1957, make the assumptions of simply supported edges, pressure only, and then look Roark for the solution.

MS for buckling? do you have any shear or compression load? In a real wing panel you have, but not from the loading condition given...

 

[LiftDivergence]

The premise of the question is also confusing. Aerodynamic pressure would certainly contribute to the stress in the skin.

However, I would expect a skin panel to primarily be sized by it's ability to take tension and shear loads as part of a box beam structure reacting wing bending loads (yes those result from the aerodynamic loads, but a skin panel cannot be accurately treated as a flat panel with only a perpendicularly oriented distributed load).

If you are interested in a real MoS I'd think you'd start with quasi-static inertial conditions for gust or maneuver an then figure out shear/moment diagrams for the wing.