In this article, a new approach has been presented in the design of a satellite attitude controller using reaction wheels. First, a PID control structure whose coefficients are dependent on the state variables is formulated and the process of extracting its constant values is explained using the Genetic Algorithm (GA) optimizer. Then, using the results of a number of tests, sufficient data for meta modeling of the system is extracted and finally the relevant control gains are extracted. A simulator platform for determination and control of satellite status based on air bearing was used to evaluate the proposed approach. Laboratory test results show that the performance of the proposed method is up to 30% better than the classical PID controller with fixed coefficients.