A finite element model of half?fairing of a new generation space vehicle with laminated nonmetal structure is built for the modal analysis. For the laboratory modal test,several methods are used to simulate the free boundary condition, such as hanging the fairing with a suspension system or putting the fairing on a sponge cushion. Model identification of half? fairing modes is done based on FRF,eigenvalues and eigenvectors. Based on test model, the finite model is updated. At last, a high?precision finite element model of satellite fairing is developed, which can be used for the analysis of fairing separation and space vehicles.