In-flight calibration of pico satellite attitude sensors via unscented kalman filter

Date

2011-07-01

Author

Söken, Halil Ersin

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In this paper an Unscented Kalman filter based procedure is proposed for the bias estimation of attitude sensors of a pico satellite. Three axis magnetometers and the rate gyros are used as attitude sensors. At the initial phase, biases of three orthogonally located magnetometers are estimated as well as the attitude and attitude rates of the satellite. During initial period after the orbit injection, gyro measurements are accepted as bias free, since the precise gyros are working accurately and the accumulated gyro biases are negligible. At the second phase, estimated constant magnetometer bias components are taken into account and the algorithm is run for the estimation of the gyro biases that are cumulatively increased by time. As a result, six different bias terms for two different sensors are obtained in two stages where attitude and attitude rates are estimated regularly. For both estimation phases of the procedure Unscented Kalman Filter is used as the estimation algorithm. © 2011 Pleiades Publishing, Ltd.,.

Subject Keywords

Control and Systems Engineering, Electrical and Electronic Engineering, General Computer Science

URI

https://hdl.handle.net/11511/69750

Journal

Gyroscopy and Navigation

DOI

https://doi.org/10.1134/s2075108711030114

Collections

Department of Aerospace Engineering, Article

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Citation Formats

H. E. Söken, “In-flight calibration of pico satellite attitude sensors via unscented kalman filter,” Gyroscopy and Navigation, pp. 156–163, 2011, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/69750.