Mathematical model attitude estimation using Kalman filter technique for low earth orbit satellite

Abstract

In space, the attitude analysis of a satellite is constantly being computed within the system of the satellite. In this paper, the linear mathematical model of the satellite attitude control with gravity gradient moment, which is inherent in low-orbit satellite is derived. Additionally, attitude estimation using the Kalman Filter technique is employed to predict the actual satellite’s attitude despite the disturbance presence in the system. As for demonstration purpose, a simulation of the satellite’s attitude under gravity gradient moment, and the attitude estimation via Kalman Filter is carried out using MATLAB software. The simulation results show that the initial conditions affect the satellite’s attitude, and attitude estimation process is important to estimate the actual satellite’s attitude despite of disturbance presence.