Application of partial differential equation modeling of the control/structural dynamics of flexible spacecraftPartial differential equations for modeling the structural dynamics and control systems of flexible spacecraft are applied here in order to facilitate systems analysis and optimization of these spacecraft. Example applications are given, including the structural dynamics of SCOLE, the Solar Array Flight Experiment, the Mini-MAST truss, and the LACE satellite. The development of related software is briefly addressed.
Taylor, Lawrence W., Jr. (NASA Langley Research Center Hampton, VA, United States)
Rajiyah, H. (General Electric Co., Astro-Space Div., Princeton NJ, United States)
August 15, 2013
January 1, 1991
Publication: In: Spaceflight mechanics 1991; Proceedings of the 1st AAS(AIAA Annual Spaceflight Mechanics Meeting, Houston, TX, Feb. 11-13, 1991. Pt. 1 (A93-17901 05-13)