Hostname: page-component-848d4c4894-sjtt6 Total loading time: 0 Render date: 2024-06-20T03:01:21.607Z Has data issue: false hasContentIssue false
  • English
  • Français

A Markley Variables-based Attitude Estimation Method Using Optical Flow and a Star Vector for Spinning Spacecraft

Published online by Cambridge University Press:  06 August 2018

Xiaolin Ning ,
Zonghe Ding ,
Mingzhu Xu ,
Jiancheng Fang  and
Gang Liu
Xiaolin Ning
Affiliation:
(School of Instrumentation Science & Opto-electronics Engineering, BeiHang University (BUAA), Beijing 100191, China) (Science and Technology on Inertial Laboratory, Fundamental Science on Novel Inertial Instrument & Navigation System Technology Laboratory, Beijing 100191, China)
Zonghe Ding*
Affiliation:
(School of Instrumentation Science & Opto-electronics Engineering, BeiHang University (BUAA), Beijing 100191, China)
Mingzhu Xu
Affiliation:
(School of Instrumentation Science & Opto-electronics Engineering, BeiHang University (BUAA), Beijing 100191, China)
Jiancheng Fang
Affiliation:
(School of Instrumentation Science & Opto-electronics Engineering, BeiHang University (BUAA), Beijing 100191, China) (Science and Technology on Inertial Laboratory, Fundamental Science on Novel Inertial Instrument & Navigation System Technology Laboratory, Beijing 100191, China)
Gang Liu
Affiliation:
(School of Instrumentation Science & Opto-electronics Engineering, BeiHang University (BUAA), Beijing 100191, China) (Science and Technology on Inertial Laboratory, Fundamental Science on Novel Inertial Instrument & Navigation System Technology Laboratory, Beijing 100191, China)
*
(E-mail: celenavbuaa@sina.cn)
Get access Rights & Permissions [Opens in a new window]

Abstract

Markley variables have advantages of slow variation, easy numerical integration and high precision in describing the attitude of spinning spacecraft. Previous attitude estimation methods based on Markley variables for spinning spacecraft usually employ a sun vector from the sun sensor, a magnetic vector from the magnetometer, or the angular rate from the gyro as the measurement. This paper proposes a Markley variables-based attitude estimation method using optical flow and a star vector from a star sensor as the measurement, where optical flow provides rate information and the star vector provides direction information. This method can estimate the direction of the spin axis and spin angular rate very well by using only one star sensor. In addition, the star sensor has higher accuracy than the traditional sun sensor and magnetometer, and the star sensor can also replace the gyro in case the gyro is out of action. The impact factors of this method are also analysed, which include spin angular rate, spin axis orientation and spacecraft moment of inertia tensor error.

Keywords

Spinning spacecraftMarkley variablesOptical flowStar vectorAttitude estimation
Type
Research Article
Information
The Journal of Navigation , Volume 71 , Issue 6 , November 2018 , pp. 1589 - 1598
Copyright
Copyright © The Royal Institute of Navigation 2018 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

REFERENCES

Chen, F., Kang, D. J. and Park, J. H. (2013). New measurement method of Poisson's ratio of PVA hydrogels using an optical flow analysis for a digital imaging system. Measurement Science & Technology, 24(5), 215–220.Google Scholar
Fasano, G., Rufino, G., Accardo, D. and Grassi, M. (2013). Satellite angular velocity estimation based on star images and optical flow techniques. Sensors, 13(10), 12771–12793.Google Scholar
Ha, J. C. V. D (2010). Spin-Axis Attitude Determination Using In-Flight Data. Journal of Guidance Control & Dynamics, 33(3), 768–781.Google Scholar
He, W., Yan, Z., Sun, C. and Chen, Y. (2017). Adaptive Neural Network Control of a Flapping Wing Micro Aerial Vehicle With Disturbance Observer. IEEE Transactions on Cybernetics, 47(10), 3452–3465.Google Scholar
Kumar, P., Kumar, S. and Raman, B. (2016). A fractional order variational model for the robust estimation of optical flow from image sequences. Optik-International Journal for Light and Electron Optics, 127(20), 8710–8727.Google Scholar
Li, Y., Yi, K. and Guan, P. (2005). The determination of attitude and control strategies for double spin geostationary satellites. Journal of Spacecraft TT& C Technology, 24(5), 19–26.Google Scholar
Markley, F. L. (1993). New dynamic variables for momentum-bias spacecraft. Journal of the Astronautical Sciences, 41(4), 557–567.Google Scholar
Markley, F. L. and Sedlak, J. E. (2007). Kalman Filter for Spinning Spacecraft Attitude Estimation. AIAA Guidance, Navigation, and Control Conference, 4608–4623, Hilton Head, SC, United States.Google Scholar
Markley, F. L. and Sedlak, J. E. (2008). Kalman Filter for Spinning Spacecraft Attitude Estimation. Journal of Guidance Control & Dynamics, 31(6), 1750–1760.Google Scholar
Ning, X., Bai, X. and Jiang, L. (2013). New Method for Attitude Determination of Spin Satellite Based on Continuous Star Map Observation. Chinese Space Science & Technology, 33(6), 49–57.Google Scholar
Pal, M. and Bhat, M. S. (2013). Star sensor based spacecraft angular rate estimation independent of attitude determination. IEEE International Conference on. Control Applications (CCA), 580–585, Hyderabad, India.Google Scholar
Sedlak, J. E. (2005). Spinning Spacecraft Attitude Estimation Using Markley Variables: Filter Implementation and Results. Nasa Goddard Space Flight Center Cp.Google Scholar
Shuster, M. D. (1993). A survey of attitude representations. The Journal of the Astronautical Sciences, 41(4), 439–517.Google Scholar
Simon, D. (2006). Optimal State Estimation: Kalman, H Infinity, and Nonlinear Approaches. Wiley-Interscience.Google Scholar
Slavinskis, A., Kvell, U., Kulu, E., Sünter, I., Kuuste, H., Lätt, S., Voormansik, K. and Noorma, M. (2014). High spin rate magnetic controller for nanosatellites. Acta Astronautica, 95(5), 218–226.Google Scholar
Soken, H. E., Sakai, S., Asamura, K., Nakamura, Y. and Takashima, T. (2016). Spin-Axis Tilt Estimation for Spinning Spacecraft. AIAA Guidance, Navigation and Control Conference, 1–15, San Diego, California, USA, doi:10.2514/6.2016-0626.Google Scholar