No abstract

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