Structural and Control Interaction for a LSS Attitude Control System Using Thrusters and Reaction Wheels
- Paper number
IAC-05-C2.2.05
- Author
Dr. Ijar M. Da Fonseca, Instituto Nacional de Pesquisas Espaciais (INPE), Brazil
- Coauthor
Mr. Peter M. Bainum, Howard University, United States
- Coauthor
Dr. Adenilson Da Silva, Instituto Nacional de Pesquisas Espaciais (INPE), Brazil
- Year
2005
- Abstract
This work provides some important information about Control Structure Interaction (CSI) for a large space structure (LSS) attitude control subsystem (ACS) comprised of thrusters and reaction wheels. The LSS physical model is assumed as a rigid long tubular beam as the main bus with two attached long flexible solar panels. The thrusters are used for large amplitude maneuvers and the reaction wheels for fine control. The Lagrange’s formulations for generalized and quasi-coordinates were used to derive the equation of motion. The gravity-gradient, the solar pressure and the drag were included in the mathematical model as external perturbations. The assumed modes discretization method has been used to model the solar array elastic displacements so as to obtain a set of ordinary differential equations to describe the LSS motion. Different control strategies were implemented to analyze the control structure interaction for two configurations, fine and coarse control. The MatLab/Simulink platform has been used for the computational simulations. The results are in agreement with the CSI theory in that thruster firings excite the solar panel vibrations and that the elastic vibration is an important issue to be taken into account for LSS ACS performance evaluation for both fine and coarse control. In spite of the control structure interaction the maneuver objectives have been accomplished with results that meet the mission criteria.
- Abstract document
- Manuscript document
IAC-05-C2.2.05.pdf (🔒 authorized access only).
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