Autonomous Navigation of MegSat1: Attitude, Sensor Bias and Scale Factor Estimation by EKF and Magnetometer-Only Measurement

Proceedings of the 2014 6th International Conference on Electronics, Computers and Artificial Intelligence (ECAI)

2014

Magnetometers are widely used for attitude determination of the low Earth orbit satellites. In order to estimate the satellite attitude accurately, bias of magnetometer must be estimated. In this study a linear Kalman filter based algorithm for estimation of magnetometer biases is proposed. We present computer technology for onboard signal processing and in-flight calibration of a low-cost strap-down inertial navigation system (SINS) for small land-survey satellite. For the system with small financial expenditures on practical implementation, the requirements are not severe on accuracy of the attitude determination. In this situation, we have applied the SINS correction based on signals of a Sun optoelectronic sensor and magnetometer.

Section: Introductionmentioning

confidence: 99%

In-flight calibration of magnetometers and low-cost SINS for small land-survey satellite

Somov

Proceedings of the 2014 6th International Conference on Electronics, Computers and Artificial Intelligence (ECAI)

2014

“…Even, as in [10], the EKF is utilized for real-time three axis magnetometer calibration as well as the low Earth orbit determination. On the other hand, a few studies, like [11] which consider magnetometer bias estimates as a part of the attitude estimation process, do also exist. Hence they may be considered as a part of spacecraft modes where attitude data is absent.…”

Section: Introductionmentioning

confidence: 99%

“…gyros) these methods lose their significance. On the other hand, a few studies, like [11] which consider magnetometer bias estimates as a part of the attitude estimation process, do also exist. This presented method works when the magnetometers are the only onboard sensors.…”

Section: Introductionmentioning

confidence: 99%

UKF based in‐flight calibration of magnetometers and rate gyros for pico satellite attitude determination

Söken

Asian Journal of Control

2011

In this paper an unscented Kalman filter based procedure for the bias estimation of both the magnetometers and the gyros carried onboard a pico satellite, is proposed. At the initial phase, biases of three orthogonally located magnetometers are estimated as well as the attitude and attitude rates of the satellite. During the 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 an unscented Kalman filter is used as the estimation algorithm.

“…However as a drawback, used attitude parameters are not estimated by the method itself and the spacecraft dynamics are not taken into consideration in this method. On the other hand, a few studies like [11,12], which consider magnetometer bias and scale factor estimates as a part of attitude estimation process, also do exist. They handle magnetometer calibration process together with the estimation of attitude parameters.…”

Section: -P2mentioning

confidence: 99%

“…They handle magnetometer calibration process together with the estimation of attitude parameters. In reference [11] EKF is used as a part of the estimation scheme. Via an UKF based estimation algorithm, which has advantages over EKF such as absence of Jacobian calculations etc., its accuracy may be surmounted.…”

Section: -P2mentioning

confidence: 99%

In-orbit magnetometer bias and scale factor calibration

Int. J. Metrol. Qual. Eng.

2016

Abstract. Magnetometers are widely used for LEO small satellites attitude determination and control system. In order to estimate satellite dynamics and control attitude accurately, scale factor and bias of magnetometer must be estimated. In this study a linear Kalman filter (LKF) based algorithm for the estimation of magnetometer biases and scale factors is proposed. Proposed algorithms are simulated through attitude dynamics of a small satellite.