Hostname: page-component-586b7cd67f-r5fsc Total loading time: 0 Render date: 2024-11-28T16:21:41.039Z Has data issue: false hasContentIssue false
  • English
  • Français

Constrained large angle reorientation manoeuvres of a space telescope using potential functions and a variable control gain

Published online by Cambridge University Press:  27 January 2016

G. Mengali  and
A. A. Quarta
G. Mengali*
Affiliation:
University of Pisa, Pisa, Italy
A. A. Quarta*
Affiliation:
University of Pisa, Pisa, Italy
*
[email protected]
[email protected]
Get access Rights & Permissions [Opens in a new window]

Extract

In some space applications, such as satellite surveillance and communication, a spacecraft must perform accurate pointing and slewing manoeuvres, whereby the spacecraft is rotated along a large angle amplitude trajectory. In many circumstances it is also required that the sensitive payload does not intercept bright objects such as the Sun, Earth and Moon, to avoid possible damage to the optical instruments. The importance of this subject has stimulated an active research, and different approaches have been reported in the literature(1-5).

Type
Research Article
Information
The Aeronautical Journal , Volume 117 , Issue 1194 , August 2013 , pp. 807 - 821
Copyright
Copyright © Royal Aeronautical Society 2013 

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

1. Kumar, R.R. Artifcial Neural Networks in Space Station Optimal Attitude Control, World Space Congress, Washington DC, USA, 27 August - 4 September 1992, Paper IAF-92-0038.Google Scholar
2. Frakes, J.P., Henretty, D.A., Flatley, T.W., Markley, L.F., San, J.K. and Lightsey, E.G. SAMPEX Science Pointing with Velocity Avoidance, AAS/AIAA Spacefight Mechanics Meeting, Colorado Springs, CO, USA, 24-26 February 1992, Paper AAS 92-182.Google Scholar
3. Singh, G., Macala, G., Wong, E.C. and Rasmussen, R.D. A Constraint Monitor Algorithm for the Cassini Spacecraft, AIAA Guidance, Navigation, and Control Conference, New Orleans, LA, USA, August 1997, Paper AIAA 97-3526.Google Scholar
4. Sørenson, A.M. ISO Attitude manoeuvre strategies, Advances in the Astronautical Sciences, 84, 1993, pp 975–987.Google Scholar
5. Wie, B. and Barba, P.M. Quaternion feedback for spacecraft large angle manoeuvres, J Guidance, Control, and Dynamics, May-June 1985, 8, (3), pp 360–365. doi: 10.2514/3.19988.Google Scholar
6. Bilimoria, K.D. and Wie, B. Time-optimal three-axis reorientation of a rigid spacecraft, J Guidance, Control and Dynamics, May-June 1993, 16, (3), pp 446–452. doi: 10.2514/3.21030.Google Scholar
7. Shen, H. and Tsiotras, P. Time-optimal control of axisymmetric rigid spacecraft using two controls, J Guidance, Control, and Dynamics, September-October 1999, 22, (5), pp 682–694. doi: 10.2514/2.4436.Google Scholar
8. Liu, S.W. and Singh, T. Fuel/time optimal control of spacecraft manoeuvres, J Guidance, Control, and Dynamics, March-April 1997, 20, (2), pp 394–397. doi: 10.2514/2.4053.Google Scholar
9. Bryson, A.E. and Ho, Y.C. Applied Optimal Control, chap 2, Hemisphere Publishing Corporation, New York, NY, 1975, pp 117–125, ISBN: 0-891-16228-3.Google Scholar
10. Melton, R.G. Hybrid Methods for Determining Time-Optimal, Constrained Spacecraft Reorientation Manoeuvres, IAA Conference on Dynamics and Control of Space Systems, Porto, Portugal, March 2012, Paper IAA-AAS-DyCoSS1-07-08.Google Scholar
11. Melton, R.G. Numerical analysis of constrained, time-optimal satellite reorientation, Mathematical Problems in Engineering, 2012, pp 1–19, Article ID 769376. doi: 10.1155/2012/769376.Google Scholar
12. McInnes, C.R. Potential Function Methods for Autonomous Spacecraft Guidance and Control, AAS/AIAAAstrodynamics Specialist Conference, Halifax, Nova Scotia, Canada, August 1995, Paper AAS 95-447.Google Scholar
13 McInnes, C.R. Large angle slew manoeuvres with autonomous sun vector avoidance, J Guidance, Control and Dynamics, July-August 1994,17, (4), pp 875–877. doi: 10.2514/3.21283.Google Scholar
14. Radice, G. and McInnes, C.R. Constrained on-board attitude control using gas jet thrusters, Aeronaut J, December 1999, 103, (1030), pp 549–556.Google Scholar
15. Casasco, M. and Radice, G. Autonomous slew manoeuvring and attitude control using the potential function method, Advances in the Astronautical Sciences, 2003, 116, ppl745–1765.Google Scholar
16. Mengali, G. and Quarta, A.A. Spacecraft control with constrained fast reorientation and accurate pointing, Aeronaut J, February 2004,108, (1080), pp 85–91.Google Scholar
17. Hablani, H.B. Attitude commands avoiding bright objects and maintaining communication with ground station, J Guidance, Control, and Dynamics, November-December 1999, 22, (6), pp 759–767. doi: 10.2514/2.4469.Google Scholar
18. Meyer, G. Design and Global Analysis of Spacecraft Attitude Control Systems, Tech rep, NASA, March, 1, 1971, NASA TR-R-361.Google Scholar
19. Slotine, J.-J. E. and Li, W. Applied Nonlinear Control, Prentice Hall, Englewood Cliffs, NJ, USA, 1991, pp 73–74, ISBN: 0-130-40890-5.Google Scholar
20. Ali, I., Radice, G. and Kim, J. Backstepping Control Design with Actuator Torque Bound for Spacecraft Attitude Manoeuvre, J Guidance, Control and Dynamics, January-February 2010,33, (1), pp 254–259. doi: 10.2514/1.45541.Google Scholar
21. Sidi, M.J. Spacecraft Dynamics and Control: A Practical Engineering Approach, Cambridge University Press, New York, NY, USA, 1997, pp 140–141, ISBN: 0-521-78780-7.Google Scholar
22. Leech, K. and Pollock, A.M.T. ISO - The Satellite and its Data, Vol II SAI/99-082/Dc, Space Science Department of ESA, Villafranca, PO Box 50727, E-28080 Madrid, Spain, July 2000, Version 1.0.Google Scholar