The aim of the thesis is to analyze different components of a satellite structure and correlate the analytical calculation results with the test ones, according with regulations. Three different levels have been investigated: theorical bases, analytical calculation and test set up and comparison. Different coupons had been realized and tested up to failure load, to satisfy the requirement of weight and frequency; the FEM analysis has been used to model the coupons and the different structures of the satellite, then the results coming from the processing are elaborated following the guidelines provided by regulations (NASA and ESA) and compared to the results obtained from the static qualification tests.