DOI QR코드

DOI QR Code

Pyramidal reaction wheel arrangement optimization of satellite attitude control subsystem for minimizing power consumption

  • Shirazi, Abolfazl (Space Research Laboratory, Aerospace Engineering Department, K.N. Toosi University of Technology) ;
  • Mirshams, Mehran (Space Research Laboratory, Aerospace Engineering Department, K.N. Toosi University of Technology)
  • Received : 2014.04.10
  • Accepted : 2014.06.10
  • Published : 2014.06.30

Abstract

The pyramidal reaction wheel arrangement is one of the configurations that can be used in attitude control simulators for evaluation of attitude control performance in satellites. In this arrangement, the wheels are oriented in a pyramidal configuration with a tilt angle. In this paper, a study of pyramidal reaction wheel arrangement is carried out in order to find the optimum tilt angle that minimizes total power consumption of the system. The attitude control system is analyzed and the pyramidal configuration is implemented in numerical simulation. Optimization is carried out by using an iterative process and the optimum tilt angle that provides minimum system power consumption is obtained. Simulation results show that the system requires the least power by using optimum tilt angle in reaction wheels arrangement.

References

  1. Wang, B, Gong K, Yang D, and Li J., "Fine attitude control by reaction wheels using variable-structure controller". Acta Astronautica, Vol. 52 , No.8 , 2003, pp. 61.-618. DOI: 10.1016/S0094-5765(02)00133-9 https://doi.org/10.1016/S0094-5765(02)00133-9
  2. Ismail, Z. and Varatharajoo, R., "A study of reaction wheel configurations for a 3-axis satellite attitude control". Advances in Space Research, Vol. 45, No. 6, 2010, pp. 750-759. DOI: 10.1016/j.asr.2009.11.004 https://doi.org/10.1016/j.asr.2009.11.004
  3. Guo, Y., Ma, G. and Li, C., "Steering law design to control moment gyroscopes for near minimum time attitude maneuver". The 5th IEEE Conference on Industrial Electronics and Applications (ICIEA). 2010, pp. 280-285. DOI: 10.1109/ICIEA.2010.5516832 https://doi.org/10.1109/ICIEA.2010.5516832
  4. Kurokawa H., Geometric Study of Single Gimbal Control Moment Gyros [Technical report]. Mechanical Engineering Laboratory, Agency of Industrial Technology and Science, Ministry of International Trade and Industry. 1998.
  5. Downs M., Adaptive Control Applied to the Cal Poly Spacecraft Attitude Dynamics Simulator [M.Sc thesis]. California Polytechnic State University. 2009.
  6. Silva S., Applied System Identification for a Four Wheel Reaction Wheel Platform [M.Sc thesis]. California Polytechnic State University. 2008.
  7. Logan J., Control and Sensor Development on a Four- Wheel Pyramidal Reaction Wheel Platform [M.Sc thesis]. California Polytechnic State University. 2008.
  8. Sarikan, A., Aydemir, M., Yavuzoglu, E. and Ozyurt, C., "Real time digital simulation of a satellite attitude control system". International Symposium on Power Electronics Electrical Drives Automation and Motion (SPEEDAM), 2010, pp. 827-832. DOI: 10.1109/SPEEDAM.2010.5545123 https://doi.org/10.1109/SPEEDAM.2010.5545123
  9. Dai, L. and Jin, G., "A 3-axis simulator for spacecraft attitude control research". IEEE International Conference on Information and Automation (ICIA). 2010, pp. 1040-1044. DOI: 10.1109/ICINFA.2010.5512158 https://doi.org/10.1109/ICINFA.2010.5512158
  10. Steyn, W., "A dual-wheel multi-mode spacecraft actuator for near-minimum-time large angle slew maneuvers", Aerospace Science and Technology, Vol. 12, No. 7, 2008, pp. 545-554. DOI: 10.1016/j.ast.2008.01.003 https://doi.org/10.1016/j.ast.2008.01.003
  11. Cruz, G. and Bernstein D., "Adaptive spacecraft attitude control with reaction wheel actuation". American Control Conference (ACC). 2013, pp. 4832-4837.
  12. Wisniewski, R. and Kulczycki P., "Slew maneuver control for spacecraft equipped with star camera and reaction wheels", Control engineering practice, Vol. 13, No. 3, 2005, pp. 349-356. DOI: 10.1016/j.conengprac.2003.12.006 https://doi.org/10.1016/j.conengprac.2003.12.006
  13. Zheng, S. and Han B. "Investigations of an integrated angular velocity measurement and attitude control system for spacecraft using magnetically suspended double-gimbal CMGs". Advances in Space Research, Vol. 51, No. 12, 2013, pp. 2216-2228. DOI: 10.1016/j.asr.2013.01.015 https://doi.org/10.1016/j.asr.2013.01.015
  14. Scholz, C., Romagnoli, D., Dachwald, B. and Theil, S., "Performance analysis of an attitude control system for solar sails using sliding masses". Advances in Space Research, Vol. 48, No. 11, 2011, pp. 1822-1835. DOI: 10.1016/j.asr.2011.05.032 https://doi.org/10.1016/j.asr.2011.05.032
  15. Wie, B., Space vehicle dynamics and control. Reston, VA: American Institute of Aeronautics and Astronautics, 2008.
  16. Sidi, M., Spacecraft dynamics and control. 1st ed. Cambridge: Cambridge University Press; 1997.
  17. Mirshams, M., Taei, H. and Others., "A Systems Engineering Tool for Satellite Simulator Design". ASME 2010 10th Biennial Conference on Engineering Systems Design and Analysis. 2010; 5: 475-483. DOI: 10.1115/ESDA2010-25341 https://doi.org/10.1115/ESDA2010-25341
  18. Mirshams, M., Taei, H., Novin Zadeh, A. and Ebadi, F., "A 3-DoF Satellite Simulator Design and Development". 60th International Astronautical Congress. 2009; D1 (6): 9.
  19. Shengyong, T., Jinjie, W, Kun, L. and Yulin Z., "Optimal configuration design of redundant flywheels and hardwarein- the-loop simulation". 31st Chinese Control Conference(CCC). 2012, pp. 4334-4338.
  20. Shengyong, T., Xibin, C., and Yulin, Z., "Configuration optimization of four dissimilar redundant flywheels with application to IPACS", 31st Chinese Control Conference(CCC). 2012, pp. 4664-4669.

Cited by

  1. Attitude estimation and sensor identification utilizing nonlinear filters based on a low-cost MEMS magnetometer and sun sensor vol.30, pp.12, 2015, https://doi.org/10.1109/MAES.2015.150069