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Attitude estimation of satellite using the extended Kalman filter | ||
| Journal of Kufa - physics | ||
| Article 1, Volume 3, Issue 1, 2011, Pages 36-44 | ||
| Authors | ||
| M.J.F Al Bermani; Ahmed Abdul-Husain Abo Tbeegh | ||
| Abstract | ||
| Computer simulation (Simulink – Matlab 7.4.4.a ) have been developed to estimate the angular velocity and the attitude in terms of the quaternions of a proposed low earth orbit satellite from noisy measurements using the extended Kalman filter . The dynamic and Kinematic models of the rigid spacecraft were distorted by external torques (atmospheric drag, solar radiation , Earth magnetic field interaction with the dipole moment of the satellite ,…etc.) .These torques were represented by white noise .The extended Kalman filter was modeled inside the embedded Matlab function . Linearization of the state space transition matrix of the spacecraft was performed by using the Jacobian matrix . Simulation results showed that the estimated attitude parameters were approximately close to the calculated values . | ||
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