Development of a Large Lightweight Composite-Honeycomb-Sandwich Central Cylinder for Next-Generation Satellites

Abstract

An advanced design method has been developed for manufacturing large fiber-reinforced-plastic (FRP) structures to be used in next-generation satellites such as the quasi-zenith satellite (QZS). The design method enables highly accurate shape and strength predictions, including of the thermal residual stresses, without trial manufacture. The design, manufacture and tests of the satellite's main structure (verification model) are also reported. The verification model is used to make the main structure of the successfully launched QZS.