An analytical dynamic model is presented for a spacecraft with multiple large flexible structures. Based on the partial differential equations (PDEs) of the motion of the solar panel and deployable arm. the governing equations of the main-body and deployable antenna and the boundary conditions at each end point are used to obtain the frequency and mode shapes of the system. Then. https://www.remtavares.com/best-offer-Merrick-Backcountry-Grain-Free-Kitten-Pate-Canned-Wet-Cat-Food-5-5-oz-Cans-Case-of-24-p14288-limited-choice/