Active Vibration Control during Deployment of Space Structures
Active vibration control during deployment of the NASA Solar Array Flight Experiment (SAFE) structure is considered in this study. The equations of motion of the SAFE structure are derived using Hamilton's principle. The approach to damp out the deployment-induced vibration is to use a force actuator located at the tip of the structure. Two different control strategies are investigated. In the first, the deployment-induced vibration is actively controlled from 70% to 100% deployment. In the second, the force actuator is turned on for a short period of time when the deployment reaches 70% and 100%. Both strategies make use of the linear regulator theory with a prescribed degree of stability. Simulated results presented show that both strategies damp out the deployment-induced vibration effectively. However, the second control system is simpler to design and implement and is, therefore, a more practical choice.
K. Krishnamurthy and M. C. Chao, "Active Vibration Control during Deployment of Space Structures," Journal of Sound and Vibration, vol. 152, no. 2, pp. 205-218, Academic Press Inc., Jan 1992.
The definitive version is available at http://dx.doi.org/10.1016/0022-460X(92)90356-3
Mechanical and Aerospace Engineering
Keywords and Phrases
Computer Simulation; Equations Of Motion; Solar Cells; Vibrations - Control; Hamiltons Principal; NASA Solar Array Flight Experiment; Spacecraft
International Standard Serial Number (ISSN)
Article - Journal
© 1992 Academic Press Inc., All rights reserved.