Estimating Sun Vector Based on Limited In-Orbit Data

Dmytro Faizullin; Koju Hiraki; M. Cho

doi:10.15866/irease.v12i2.16189

Estimating Sun Vector Based on Limited In-Orbit Data

Dmytro Faizullin^(1*), Koju Hiraki⁽²⁾, M. Cho⁽³⁾

^(*) Corresponding author

Authors' affiliations

DOI: https://doi.org/10.15866/irease.v12i2.16189

Abstract

This paper introduces an attitude and orbit determination system, in particular a sun vector determination algorithm, for HORYU-IV nano-satellite by Kyushu Institute of Technology (Kyutech). Usually, nano-satellites cannot use sensors with high specs because of limited budget and onboard space. In order to achieve the required accuracy of attitude determination, estimation algorithms combining different sources of attitude information should be used. One of the HORYU-IV missions has required sun vector information. In order to detect the sun angle, six sun sensors, which have originally been designed and developed by the authors, and five solar panels have been used. However, due to the narrow field of view and to the saturation property of these sensors, the duration of sun detection is quite limited. At a non-detection period, a gyro sensor is used in order to propagate the attitude. However, the sensor has the bias error in its measured value. Hence, the Extended Kalman Filter has been used in order to estimate the sun vector and the bias error of gyro sensors. A simulation result shows that the algorithm can estimate the sun vector in 1deg accuracy.
Copyright © 2019 Praise Worthy Prize - All rights reserved.

Keywords

Angular Velocity; Extended Kalman Filter; Pinhole Sun Sensor; Small Satellite; Sun Vector Determination

Full Text:

PDF

References

Wertz J. ed., Spacecraft Attitude Determination and Control (the Kluwer Academic Publisher, Dordrecht, Holland, 1978).

J. Crassidis, F. Markley, Y. Cheng, Survey of nonlinear attitude estimation methods, J. Guid. Control Dyn. 30 (1) (2007) 12.

Trawny N., Roumeliotis S., Indirect Kalman Filter for 3D Attitude Estimation; University of Minnesota: Minneapolis, MN, USA, TR 2005-002, Rev. 57; March 2005.

R. Burton, S. Rock, J. Springmann, J. Cutler, Online attitude determination of a passively magnetically stabilized spacecraft, Acta Asronautica, Volume 133, April 2017, Pages 269–281.
https://doi.org/10.1016/j.actaastro.2017.01.024

A. Antonello, L. Olivieria, A. Francesconib, Development of a low-cost sun sensor for nanosatellites, Acta Asronautica, Volume 144, March 2018, Pages 429–436.
https://doi.org/10.1016/j.actaastro.2018.01.003

Sh. Nakasuka, K. Miyata, Y. Tsuruda, Discussions on attitude determination and control system for micro/nano/pico-satellites considering survivability based on Hodoyoshi-3 and 4 experiences, Acta Asronautica, Volume 145, April 2018, Pages 515–527.
https://doi.org/10.1016/j.actaastro.2018.02.006

Ewang, E., Miyahara, A., Khan, A., Toyoda, K., Cho, M., Photoelectron Current Measurement in Low Earth Orbit Using a Lean Satellite, HORYU-IV, (2017) International Review of Aerospace Engineering (IREASE), 10 (3), pp. 140-153.
https://doi.org/10.15866/irease.v10i3.12394

D. Faizullin, K. Hiraki, HORYU-IV team, M. Cho: Optimization of a sun vector determination for pinhole type sun sensor, International Journal of Research – Granthaalayah, July 2017, Vol 5 (Iss.7), pp. 54-67.

D. Faizullin, K. Hiraki, HORYU-IV team, M. Cho, Improvement of sun angle accuracy from in-orbit data of a quadrant photodiodesun sensor, International Journal of Research – Granthaalayah, May 2017, Vol 5 (Iss.7), pp. 54-67.

Ortega et al., MEMS solar sensor testing for satellite applications, 2009 Spanish Conference on Electron Devices, Santiago de Compostela, 2009, pp. 345-348.

S4349 photodiode Hamamatsu. [Online]. Available:
https://www.hamamatsu.com/eu/en/product/alpha/S/4106/S4349/index.html

G. Falbel and M. A. Paluszek, An ultra low weight/low cost three axis attitude readout system for nano-satellites, 2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542), Big Sky, MT, 2001, pp. 2469-2481 vol.5.
https://doi.org/10.1109/aero.2001.931208

D. P. Ramer and J. C. Rains Jr., Quadrant light detector, U.S. patent 5 705 804, Jan. 6, 1998.

E. Boslooper: BepiColombo Fine Sun Sensor, in Proc. ICSO 2012, Ajaccio. [Online]. Available:
http://esaconferencebureau.com/custom/icso/2012/papers/fp_icso-029.pdf

Pablo Ortega, A Miniaturized Two Axis Sun Sensor for Attitude Control of Nano-Satellites, IEEE SENSORS JOURNAL, Vol. 10 (Iss. 10), October 2010.

Mohamed Yahia Edries, A. Tanaka, E. Dashdondog, Design and Testing of Electrical Power Subsystem (EPS) of a lean satellite, Horyu-IV”, ISTS 30th conference, Kobe-Hyogo, Japan, July 2015.
https://doi.org/10.2322/tastj.14.pf_7

Mohamed Yahia Edries, M. Alkali, and Mengu Cho, Design and evaluation of a Nano-satellite Battery Charge Regulator (BCR) based on a Simple Maximum Power Point (MPP) Tracking Control, 58th (JSASS) Conference, Nagasaki, Japan, November 2014.

Habib, T., In-Orbit Spacecraft Inertia, Attitude, and Orbit Estimation Based on Measurements of Magnetometer, Gyro, Star Sensor and GPS Through Extended Kalman Filter, (2018) International Review of Aerospace Engineering (IREASE), 11 (6), pp. 247-251.
https://doi.org/10.15866/irease.v11i6.14839

Grillo, C., Montano, F., Automatic EKF Tuning for UAS Path Following in Turbulent Air, (2018) International Review of Aerospace Engineering (IREASE), 11 (6), pp. 241-246.
https://doi.org/10.15866/irease.v11i6.15122

Bakhti, M., Idrissi, B., Highly Nonlinear Flexible Manipulator State Estimation Using the Extended and the Unscented Kalman Filters, (2016) International Review of Automatic Control (IREACO), 9 (3), pp. 151-160.
https://doi.org/10.15866/ireaco.v9i3.9018

Refbacks

There are currently no refbacks.

Username
Password
Remember me