In this paper, Attitude Determination and Mol and the location of the CM with respect to the working Parameter Identification problem of a LEO satellite are reference frame [5, 6]. studied. In Attitude Determination System three rate Finally ADS and PIM are coupled. Thus ADS and PIM gyroscopes, three axis magnetometer and a sun sensor data outputs are fed to each other. are used. Using Kalman Filter algorithms angular ratesIn the following the satellite model, sensor measurement and quaternions are estimated. In these algorithms, rate models, attitude determination and parameter identification gyroscope bias measurements are also taken into algorithms and finally simulation results are given and consideration in state estimation. In Parameter discussed. Identification part, the Moment of Inertia values of the satellite are estimated by using Least Square Estimation

Large torque amplification and momentum storage capacity are the two basic properties that make control moment gyroscopes (CMGs) superior when compared to the reaction and momentum wheels commonly used in spacecraft attitude control. Software and Hardware in the Loop (HIL) tests are carried out for the verification of the requirements of CMG based attitude control systems (ACS). In order to have even a more realistic results, CMG based ACS HIL tests are performed on three axis air bearing test bed by taking into account the restrictions of the air bearing table used. The results of these simulations and tests are presented.

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