Honeycomb cored structures are considered one of the most efficient
composite structures which are commonly used in different industrial
applications. These structures are characterized by high strength to weight
ratio and good impact resistance thus it is suitable for aerospace structures.
Structural properties of honeycomb structure depend on its lower, upper
skin sheet thickness, the core material thickness, cell dimension, cell angle
and foil thickness. Using of honeycomb structure panels in satellite main
structure provide the opportunity to reduce satellite mass in significant
manner. This study concerns with the static and dynamic performance of
honeycomb sandwich panel structures and its applications in spacecraft
construction. This work studies the static and dynamics characteristics of a
spacecraft structure including an intermediate plate made of two different
materials; the first one with an Aluminum intermediate sandwich plate
while the second with honeycomb sandwich plate. The obtained results
show that the satellite structure supported with honeycomb intermediate
plate produces higher value of the fundamental resonant frequencies
compared to the corresponding ones in satellite structure with Aluminum
intermediate plate which is better for the launch vehicle requirements.
Moreover, the spacecraft structure mass was reduced by around 15%.