Journal of Mechanical Science and Technology

The Korean Society of Mechanical Engineers (대한기계학회)
권호 표지

Time Optimal Attitude Maneuver Strategies for the Agile Spacecraft with Reaction Wheels and Thrusters

  • Lee Byung-Hoon (School of Aerospace and Mechanical Engineering, Hankuk Aviation University) ;
  • Lee Bong-Un (School of Aerospace and Mechanical Engineering, Hankuk Aviation University) ;
  • Oh Hwa-Suk (School of Aerospace and Medhanical Engineering, Hankuk Aviation University) ;
  • Lee Seon-Ho (Group of Satellite Control System, Korea Aerospace Research Institute) ;
  • Rhee Seung-Wu (Group of Satellite Control System, Korea Aerospace Research Institute)
  • Published : 2005.09.01
Download PDF
⟨ Previous Next ⟩

Abstract

Reaction wheels and thrusters are commonly used for the satellite attitude control. Since satellites frequently need fast maneuvers, the minimum time maneuvers have been extensively studied. When the speed of attitude maneuver is restricted due to the wheel torque capacity of low level, the combinational use of wheel and thruster is considered. In this paper, minimum time optimal control performances with reaction wheels and thrusters are studied. We first identify the features of the maneuvers of the satellite with reaction wheels only. It is shown that the time-optimal maneuver for the satellite with four reaction wheels in a pyramid configuration occurs on the fashion of single axis rotation. Pseudo control logic for reaction wheels is successfully adopted for smooth and chattering-free time-optimal maneuvers. Secondly, two different thrusting logics for satellite time-optimal attitude maneuver are compared with each other: constant time-sharing thrusting logic and varying time-sharing thrusting logic. The newly suggested varying time-sharing thrusting logic is found to reduce the maneuvering time dramatically. Finally, the hybrid control with reaction wheels and thrusters are considered. The simulation results show that the simultaneous actuation of reaction wheels and thrusters with varying time-sharing logic reduces the maneuvering time enormously. Spacecraft model is Korea Multi-Purpose Satellite (KOMPSAT)-2 which is being developed in Korea as an agile maneuvering satellite.

Keywords

References

  1. Bilimoria, K. D. and Wie, B., 1993, 'Time Optimal Three-Axis Reorientation of a Rigid Spacecraft,' Journal of Guidance, Control, and Dynamics, Vol. 16, No. 3, pp. 446-452 https://doi.org/10.2514/3.21030
  2. Byers, R. M. and Vadali, S. R., 1993, 'Quasi-Closed-Form Solution to the Time-Optimal Rigid Spacecraft Reorientation Problem,' Journal of Guidance, Control and Dynamics, Vol. 16, No. 3, pp. 453-461 https://doi.org/10.2514/3.21031
  3. Hurtado, J. E. and Junkins, J. L., 1998, 'Optimal Near-Minimum-Time Control,' Journal of Guidance, Control, and Dynamics, Vol. 21, No. 1, pp. 172-174 https://doi.org/10.2514/2.4214
  4. KARI and HAU, 2003, 'Varying Time Division Pulsing Method and its Controller for Coupled Thrusting Satellite,' Patent Pending in Korea
  5. Lee, B. H., 2004, 'Time Optimal Attitude Maneuvers for Agile Spacecraft with Thrusters and Reaction Wheels,' Thesis, M.S., Department of Aerospace and Mechanical Engineering, Hankuk Aviation University, Korea
  6. Malcolm, D. S., 1993, 'A Survey of Attitude Representations,' Journal of the Astronautical Sciences, Vol. 41, No. 4, pp. 439-517
  7. Oh, H. S., 1999, 'Attitude Control by Asymmetric Thrusters' Independent Off Modulation During Orbit Adjustment Maneuvers,' Journal of Astronomy and Space Sciences in Korea, Vol. 16, No. 2, pp. 265-272
  8. Oh, H. S. and Hwang, J. H., 1999, 'Minimum Fuel Back-Up Attitude Control and Momentum Dumping of a Satellite with an Asymmetric Thruster Configuration,' Journal of Korean Society for Aeronautical and Space Sciences in Korea, Vol. 27, No. 6, pp. 105-115
  9. Oh, H. S., Kwon, J. W., Lee, H., Nam, M. R. and Park, D. J., 2001, 'Torque and Force Measurement of a Prototype HAU Reaction Wheel and the Effect of Disturbance on the Attitude Stability of spacecraft,' KSME International Journal, Vol. 15, No. 6, pp. 743-751
  10. Oh, H. S. and Cheon, D. I., 2005, 'Precision Measurements of Reaction Wheel Disturbances with Frequency Compensation Process,' Journal of Mechanical Science and Technology, KSME, Vol. 19, No. 1, pp. 136-143 https://doi.org/10.1007/BF02916112
  11. Scrivener, S. L. and Thomson, R. C., 1993, 'Time Optimal Reorientation of a Rigid Spacecraft using Collocation and Nonlinear Programming,' Advances in the Astronautical Sciences, Vol. 85, No. 3, pp. 1905-1924
  12. Seywald, H. and Kumar, R. R., 1993, 'Singular Control in Minimum Time Spacecraft Reorientation,' Journal of Guidance, Control and Dynamics, Vol. 16, No. 4, pp. 686-694 https://doi.org/10.2514/3.56607
  13. Shen, H. and Tsiotras, P., 1999, 'Time-Optimal Control of Axi-symmetric Rigid Spacecraft Using Two Controls,' Journal of Guidance, Control, and Dynamics, Vol. 22, No. 5, pp. 682-694 https://doi.org/10.2514/2.4436
  14. Sidi, M., 1997, Spacecraft Dynamics and Control, Cambridge University Press, pp. 287-289
  15. Steyn, W. H., 1995, 'Near-Minimum-Time Eigenaxis Rotation Maneuvers Using Reaction Wheels,' Journal of Guidance, Control and Dynamics, Vol. 18, No. 5, pp. 446-452