Lighter and stiffer structural construction is required for space
rockets than those used in aviation. A reduction of only 1 Kg in
the weight of a rocket intended for a flight to Mars and back
results in saving 2 tons of propellant. At present, sandwich
technology is extensively used in Aeronautics and Aerospace fields.
Sandwich panels with thin composite face sheets are used due to
their ability to produce structures with high stiffness to weight
and strength to weight ratios. In this research, Finite Element
(FE) model is generated for a particular test configuration of
honeycomb sandwich structure with metallic (Aluminium) skins. In
this modelling effort, the specimen is modelled in such a way to
simulate and analyze in a true sense. Stability and non linear
analysis is carried out using FEA software SAMCEF. With geometric
and material nonlinearity, the results are then compared with the
experimental ones. Force displacement curves acquired from FEA and
3point bending test seem good enough for comparison.
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