International Journal on Science and Technology

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Attitude Control and Navigation of Low Earth Orbit Satellite

Author(s) Seda (Karadeniz) Kartal
Country Turkey
Abstract In this study, the orbit and attitude model of a low Earth orbit satellite has been developed. The attitude model is addressed both dynamically and kinematically, and the quaternion parameters and Euler angles of the satellite are obtained. Noise is added to this attitude information to generate sensor data for the INS (Inertial Navigation System) and GPS (Global Positioning System). The attitude information is estimated by combining the two-sensor data with INS/GPS integrated navigation system using an Extended Kalman Filter algorithm. To control the satellite's attitude, a DC motor model driving the reaction wheels is created, and the angular velocity and torque of the motor are controlled. A PID controller is designed for satellite attitude control. The optimal gain coefficients of the PID controller are determined by minimizing the difference between the integrated navigation system output and the desired attitude information. By generating reference inputs for the satellite model, the satellite's attitude is controlled. The results show that in the integrated system, consisting of satellite orbit, attitude model, navigation, and control design, the satellite reaches the desired attitude quickly and stably. The entire study is carried out in the MATLAB/Simulink environment.
Keywords Low Earth Orbit Satellite, Control, Navigation, INS/GPS integration, PID.
Field Engineering
Published In Volume 16, Issue 1, January-March 2025
Published On 2025-02-24
DOI https://doi.org/10.71097/IJSAT.v16.i1.2033
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