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The Attitude Control Problem for Flexible Satellites
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English
Abstract
An attitude control system for a flexible satellite is investigated. It is assumed that the satellite can be analyzed, at least to a first approximation, as a thin circular plate. Certain types of orbiting telescopes fall in this category. The modes of vibration of this system are determined and their influence on the performance quality of a three axis control system is studied. Essential complications in the analysis stem from the non-linear gyroscopic coupling terms as well as the coupling of rigid body and elastic motion.
It is shown that the elastic motions are reflected on only one axis of the vehicle with proper location of sensors, and that the control system can be made insensitive to the two lowest vibration modes. Furthermore, the inter axis coupling has negligible influence on the system stability if the control system for each axis is properly designed.
Authors
Citation
Greensite, A., "The Attitude Control Problem for Flexible Satellites," SAE Technical Paper 650584, 1965, https://doi.org/10.4271/650584.Also In
References
- Rayleigh, J. W. “The Theory of Sound” 1894 Dover New York
- Roberson, R. E. “Attitude Control of Satellites and Space Vehicles” Advances in Space Sciences Vol. 2 Academic Press Inc. New York 1960
- Vaeth, J. E. “Flywheel Control of Space Vehicles” IRE Convention Record March 1960
- Courant, R. Hilbert, D. “Methods of Mathematical Physics” Vol. 1 Intersclence Publishers New York 1953
- Schmitt, A. F. et. al., “Approximate Transfer Functions for Flexible Booster and Autopilot Analysis” WADD TR-61-93 April 1961
- Leondes, C. T. Roberson, R. E. Aoki, M. “Analysis and Synthesis of a Particular Class of Satellite Attitude Control Systems” J. Aero. Sci. Vol. 29 1962 1433