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In this study, the design of an electro-mechanical fin loading system which is utilized to simulate the effects of the aerodynamic moment occurring in an atmospheric flight on a missile system is dealt with. In this extent, the dynamic modeling of the dedicated loading system is constructed and then the control system is designed on that model. As the control algorithm, the classical control system operating with regard of the PID (proportional plus integral plus derivative) control action and the robust control system designed according to the H∞ norm are taken into consideration. Once the mentioned control systems are built, the relevant computer simulations are performed with the inclusion of a realistic control actuation system model in accordance with the consistent numerical values of the necessary parameters. As a result of this work, it is observed that the robust control system yields more satisfactory results than its classical counterpart even under more severe conditions.