When designing the skin metal plates of a light aircraft under pressure we get relatively high deformations, apart from aerodynamic considerations and shear buckling due to shear flow can we just use one of the design philosophy approximations to reduce deflections and avoid narrow rib spacing, stringers
1. higher load factors are transient , so compute the deflections under 1g load condition
2. may be considering fatique and depending on the stiffness of the perimeter supports (ribs, front and rear spars ) use max load factor and large deformation theory to reduce deflections allowing in plane forces in the plate,
before having several lower back surgeries i had a light aircraft, as an amateur flying engineer i hated to see those wrinkles on the upper skin during gusty conditions,
Any source and/or advice all are welcome
thank you
1. higher load factors are transient , so compute the deflections under 1g load condition
2. may be considering fatique and depending on the stiffness of the perimeter supports (ribs, front and rear spars ) use max load factor and large deformation theory to reduce deflections allowing in plane forces in the plate,
before having several lower back surgeries i had a light aircraft, as an amateur flying engineer i hated to see those wrinkles on the upper skin during gusty conditions,
Any source and/or advice all are welcome
thank you
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