PD controller for three-axis satellite attitude control using discrete Kalman Filter

This paper explains driving a six-state discrete Kalman Filter to estimate angular rates of satellite base on control sensor noisy data. A typical satellite is assumed in a special orbit and orbital angular velocity and orbital angular acceleration are established. For completion of simulation linear dynamics model of satellites and environment disturbances model such as solar pressure and gravity gradient torque are derived. The simulation is progressed at discrete ten seconds, which assumed as the data updating rate from sensor. Noisy measurements are produced by sensor and these data are sent to the discrete Kalman Filter part to estimate the attitude and attitude rate. Final results indicate that these rate estimates are appropriate for space missions.