Mainly solves the problem about choice of stiffened structure configuration of laminated composite fuselage. In this paper, the finite element model of the structure was modeled in Patran and analyzed preliminarily by Nastran to get the element force. Then the finite element model is imported into Hypersizer to calculate and optimize, then the optimal stiffened structure type of laminated composite fuselage is attained. The research of modeling, analysis and optimization has practicable engineering value.