Extended Kalman Filter Based Estimations for Satellite Attitude Control System
نویسندگان
چکیده
This paper mainly focuses on the maneuver of satellite in orbit. A non-linear multi-inputs multi-outputs model has been derived from Newton-Euler equations motion. The dynamics is presented with control methodologies allowing Extended Kalman Filter (EKF) to iteratively provide improved data sets zero errors. As system distracted atmospheric swings which are random hence problem stochastic disturbance furnished. set differential two dimensional Ito type used for modeling said disturbances (before t = 4s recorded). attitude parameters recorded RT-LAB setup providing adequately superior estimation outcome thereby makes filter more appealing. With presence Gaussian noise both dimension and system, gives correct estimates. It’s collaboration hardware commendable. Hence, an deals such nonlinear models proves be a higher choice achieving best online results. comparison reflecting tracking stable designed advanced adaptive robust controller (AARC) situations plotted. priority making also visited. Also, use three different values confounding variables revealed that weighting line completely diminished boosting when Moreover, previous research involves methods improve communication ground station, this exact positioning concerned its validation tested experimentally OPAL-RT hardware. To sum up, development controllers have encouraged stability accuracy systems considering varying conditions. simulation results predict perfect output respect desired set-point proposed controller.
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ژورنال
عنوان ژورنال: International journal of engineering and advanced technology
سال: 2021
ISSN: ['2249-8958']
DOI: https://doi.org/10.35940/ijeat.e2592.0610521