Design of smart microsatellite deployable solar wings

摘要

This paper deals with the design of four deployable solar wings for the Scientific Microsatellite for Advanced Research and Technology (SMART). IN order to minimize the ms-to-exposed-surface ratio of the solar wings,. A Sandwich configuration is chosen with carbon fiber reinforced plastic (CFRP) skins and aluminum honeycomb Core. Desired thermal-structural properties are obtained by adequate selection of materials, fiber content, lay-up, Honeycomb cell size.