Pseudo-linear approach to nanosatellite attitude estimation and magnetometer calibration

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Pseudo-linear approach to nanosatellite attitude estimation and magnetometer calibration. / Khurshid, Osama; Selkainaho, Jorma; Kallio, Esa; Visala, Arto; Soken, Halil Ersin.

Proceedings of 8th International Conference on Recent Advances in Space Technologies, RAST 2017. Institute of Electrical and Electronics Engineers, 2017. p. 355-360 8003008.

Research output: Chapter in Book/Report/Conference proceedingConference contributionScientificpeer-review

Harvard

Khurshid, O, Selkainaho, J, Kallio, E, Visala, A & Soken, HE 2017, Pseudo-linear approach to nanosatellite attitude estimation and magnetometer calibration. in Proceedings of 8th International Conference on Recent Advances in Space Technologies, RAST 2017., 8003008, Institute of Electrical and Electronics Engineers, pp. 355-360, International Conference on Recent Advances in Space Technologies, Istanbul, Turkey, 19/06/2017. https://doi.org/10.1109/RAST.2017.8003008

APA

Khurshid, O., Selkainaho, J., Kallio, E., Visala, A., & Soken, H. E. (2017). Pseudo-linear approach to nanosatellite attitude estimation and magnetometer calibration. In Proceedings of 8th International Conference on Recent Advances in Space Technologies, RAST 2017 (pp. 355-360). [8003008] Institute of Electrical and Electronics Engineers. https://doi.org/10.1109/RAST.2017.8003008

Vancouver

Khurshid O, Selkainaho J, Kallio E, Visala A, Soken HE. Pseudo-linear approach to nanosatellite attitude estimation and magnetometer calibration. In Proceedings of 8th International Conference on Recent Advances in Space Technologies, RAST 2017. Institute of Electrical and Electronics Engineers. 2017. p. 355-360. 8003008 https://doi.org/10.1109/RAST.2017.8003008

Author

Khurshid, Osama ; Selkainaho, Jorma ; Kallio, Esa ; Visala, Arto ; Soken, Halil Ersin. / Pseudo-linear approach to nanosatellite attitude estimation and magnetometer calibration. Proceedings of 8th International Conference on Recent Advances in Space Technologies, RAST 2017. Institute of Electrical and Electronics Engineers, 2017. pp. 355-360

Bibtex - Download

@inproceedings{c42c588b05fb4e04a4ded6103caa4936,
title = "Pseudo-linear approach to nanosatellite attitude estimation and magnetometer calibration",
abstract = "This paper presents the pseudo-linear estimation approach to the high-rate spinning small spacecraft attitude estimation problem. The sensor suit utilised in the presented approach uses gyro, magnetometer and sun-sensor measurements. The presented estimation technique has been designed particularly for the problem of attitude determination during the Aalto-1 nanosatellite's Plasma Brake Experiment (PBE). The design of the PBE demands the satellite to be spun up to 200 deg/s for deploying the tether by the use of centrifugal force resulting from the spin motion. The spinning up of the satellite is achieved only through the magnetic actuation. The used spin controller has been proven to be very robust for different initial conditions and operating scenarios. However, it demands accurate attitude estimates in order to efficiently and successfully spin the satellite up to the required angular velocity. Magnetometers are the most important sensors amongst the available onboard for the presented setup. The reason for this is that the system has the inputs only from the magnetometers and gyros during the eclipse period. It is necessary to estimate the magnetometer biases because the systems are very closely integrated and there is a higher risk of electromagnetic interference in them. A pseudo-linear Kalman Filter (PSLKF) has been studied. The two cases of integrated and separate attitude estimation and magnetometer calibration algorithms have been studied and analyzed in the perspective of their use onboard a nanosatellite.",
keywords = "attitude estimation, nanosatellite, pseudo-linear Kalman filter",
author = "Osama Khurshid and Jorma Selkainaho and Esa Kallio and Arto Visala and Soken, {Halil Ersin}",
year = "2017",
month = "8",
day = "4",
doi = "10.1109/RAST.2017.8003008",
language = "English",
pages = "355--360",
booktitle = "Proceedings of 8th International Conference on Recent Advances in Space Technologies, RAST 2017",
publisher = "Institute of Electrical and Electronics Engineers",
address = "United States",

}

RIS - Download

TY - GEN

T1 - Pseudo-linear approach to nanosatellite attitude estimation and magnetometer calibration

AU - Khurshid, Osama

AU - Selkainaho, Jorma

AU - Kallio, Esa

AU - Visala, Arto

AU - Soken, Halil Ersin

PY - 2017/8/4

Y1 - 2017/8/4

N2 - This paper presents the pseudo-linear estimation approach to the high-rate spinning small spacecraft attitude estimation problem. The sensor suit utilised in the presented approach uses gyro, magnetometer and sun-sensor measurements. The presented estimation technique has been designed particularly for the problem of attitude determination during the Aalto-1 nanosatellite's Plasma Brake Experiment (PBE). The design of the PBE demands the satellite to be spun up to 200 deg/s for deploying the tether by the use of centrifugal force resulting from the spin motion. The spinning up of the satellite is achieved only through the magnetic actuation. The used spin controller has been proven to be very robust for different initial conditions and operating scenarios. However, it demands accurate attitude estimates in order to efficiently and successfully spin the satellite up to the required angular velocity. Magnetometers are the most important sensors amongst the available onboard for the presented setup. The reason for this is that the system has the inputs only from the magnetometers and gyros during the eclipse period. It is necessary to estimate the magnetometer biases because the systems are very closely integrated and there is a higher risk of electromagnetic interference in them. A pseudo-linear Kalman Filter (PSLKF) has been studied. The two cases of integrated and separate attitude estimation and magnetometer calibration algorithms have been studied and analyzed in the perspective of their use onboard a nanosatellite.

AB - This paper presents the pseudo-linear estimation approach to the high-rate spinning small spacecraft attitude estimation problem. The sensor suit utilised in the presented approach uses gyro, magnetometer and sun-sensor measurements. The presented estimation technique has been designed particularly for the problem of attitude determination during the Aalto-1 nanosatellite's Plasma Brake Experiment (PBE). The design of the PBE demands the satellite to be spun up to 200 deg/s for deploying the tether by the use of centrifugal force resulting from the spin motion. The spinning up of the satellite is achieved only through the magnetic actuation. The used spin controller has been proven to be very robust for different initial conditions and operating scenarios. However, it demands accurate attitude estimates in order to efficiently and successfully spin the satellite up to the required angular velocity. Magnetometers are the most important sensors amongst the available onboard for the presented setup. The reason for this is that the system has the inputs only from the magnetometers and gyros during the eclipse period. It is necessary to estimate the magnetometer biases because the systems are very closely integrated and there is a higher risk of electromagnetic interference in them. A pseudo-linear Kalman Filter (PSLKF) has been studied. The two cases of integrated and separate attitude estimation and magnetometer calibration algorithms have been studied and analyzed in the perspective of their use onboard a nanosatellite.

KW - attitude estimation

KW - nanosatellite

KW - pseudo-linear Kalman filter

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U2 - 10.1109/RAST.2017.8003008

DO - 10.1109/RAST.2017.8003008

M3 - Conference contribution

SP - 355

EP - 360

BT - Proceedings of 8th International Conference on Recent Advances in Space Technologies, RAST 2017

PB - Institute of Electrical and Electronics Engineers

ER -

ID: 15847318