Z-SAT uses passive gravity-gradient, along with active magnetorquer stabilization methods to control of attitude. To modify the ratios of moments of inertia, control boom has been selected. It is a deployable mechanism. Several restrictions, such as stability, strength, and thermal distortion, have been considered to optimum design. In this paper, the relevant design process is described. Proper configuration of the boom is determined ; then the stability analysis is done on the satellite (along with boom), to make sure that the system would deliver the right response. Combination of analyses mentioned above results in optimum geometrical, physical, and timing characteristics of control boom of Z-SAT.