Attitude estimation of satellite using the extended Kalman filter
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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Copyright (c) 2011 M.J.F Al Bermani, Ahmed Abdul-Husain Abo Tbeegh
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