Hostname: page-component-848d4c4894-sjtt6 Total loading time: 0 Render date: 2024-06-22T19:43:17.599Z Has data issue: false hasContentIssue false
  • English
  • Français

Dynamic analysis of flexible space vehicles having uncoupled control axes

Published online by Cambridge University Press:  04 July 2016

D. R. Smart ,
K. F. Gill ,
J. M. Gething  and
J. A. Holt
D. R. Smart
Affiliation:
Electronic and Space Systems Group, BAC, GW Division, Filton, Bristol
K. F. Gill
Affiliation:
Department of Mechanical Engineering, The University, Leeds
J. M. Gething
Affiliation:
Scientific Services Department, CEGB, Portishead, Bristol
J. A. Holt
Affiliation:
Electronic and Space Systems Group, BAC, GW Division, Filton, Bristol
Get access Rights & Permissions [Opens in a new window]

Extract

Increasingly stringent attitude stabilisation requirements are the current trend in both experimental and commercial satellites as is seen in the current Intelsat, ESRO and UK communication studies. These craft must be lightweight, compact and rugged during the launch phase but after mission capture such requirements no longer apply. The increasingly high power requirements of such craft are met by the use of large flexible solar arrays which are packed away during launch and unfurl when the craft becomes operational. For the three-axis stabilised craft being studied reaction jets are used to achieve the high pointing accuracy required. Such actuators may be hot or cold gas systems or in the future may be electric engines’. The broad spectral content of these actuators will inevitably excite modes of vibration in a wide range of frequencies. The influence of these highly resonant modes on the performance of on-board controllers, needing a relatively high bandwidth of 0-10 Hz, to achieve high pointing accuracy of up to a few seconds of arc may lead to design difficulties.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 78 , Issue 768 , December 1974 , pp. 560 - 569
Copyright
Copyright © Royal Aeronautical Society 1974 

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. Hughes, W. G. Active stabilisation. AGARD Lecture series No 45 on Attitude stabilisation of satellites in orbit.Google Scholar
2. Likins, P. W. and Fleischer, G. E. Results of flexible spacecraft attitude control studies utilising hybrid co ordinates. AIAA paper 70–20.Google Scholar
3. Likins, P. W. Dynamics and control of flexible space vehicles. TR 32-1329, Jet Propulsion Lab, 1970.Google Scholar
4. P. W., Likin and Gale, A. H. Analysis of interactions between attitude control systems and flexible appendages. Proc of the 15th international Astronautical Congress, (Belgrade, 1968), vol 2. Pergamon Press, 1970. pp 67–90.Google Scholar
5. Gale, A. H. and Likins, P. W. Influence of flexible appendages on dual-spin spacecraft dynamics and control. of Spacecraft and Rockets, vol 7, pp 1049–1056, 1970.Google Scholar
6. Likins, P. W. Modal method for analysis of free rotation of spacecraft. AIAA Journal, vol 5, No 7, pp 1304–1308.Google Scholar
7. Liking, P. W. and Wirsching, Paul H. Use of synthetic modes in hybrid co-ordinate dynamic analysis. AIAA Journal, vol 6, No 10, October, 1968.Google Scholar
8. Hooker, and Mirgulies, . The dynamical attitude equation for an n-Body satellite. Journal of Aeronautical Sciences, vol XII, No 4, pp 123–128.Google Scholar
9. Nicklas, J. C. and Vivian, H. C. Derived-rate increment stabilisation: its application to attitude control problems. ASME Journal of Basic Engineering, 84, 54–60 (1962).Google Scholar
10. Maclaren, A. P. Design of a gas-jet attitude control system for use in satellites. RAE Technical note Space 54 (1964).Google Scholar
11. Melcher, H. J. and Otlen, D. D. Modulating bong-bong attitude controls. Control Engineering, 73–75, November 1965.Google Scholar
12. Scott, E. D. Pseudo-rate sawtooth pulse reset control system analysis and design. AIAA/JACC Guidance and Control Conference Preprint, August 1966.Google Scholar
13. Gaylord, R. S. and Keller, W. N. Attitude control systems using logically controlled pulses. Presented at AS Guidance, Control, and Navigation Conference, Stanford, Calif, Aug 7-9, 1961.Google Scholar
14. Kroy, W. H. Divergence of minimum impulse attitude control system under external torque. Douglas Report No SM-47751, November 1964.Google Scholar
15. Wilkinson, J. H. The Algebraic Eigen value problem. Clarendon Press, Oxford 1965.Google Scholar
16. Smart, D. R. Dynamic Analysis and 3-Axis Attitude Control of a Flexible Space Vehicle. PhD Thesis, Dept of Mechanical Engineering, University of Leeds, June 1973.Google Scholar