Abstract
Advanced design method for manufacturing large Fiber-Reinforced-Plastics structure, such as next generation satellites like
quasi-zenith satellite, is developed. The design method enables high shape accuracy, strength prediction including thermal residual stresses without
trial manufactures. The design, manufacturing, and tests of a satellite main structure (verification model) are reported. The verification model was
used as main structure of Quasi-Zenith Satellite and successfully launched.
