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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.
Document ID
19930033933
Document Type
Conference Paper
Authors
Taylor, Lawrence W., Jr. (NASA Langley Research Center Hampton, VA, United States)
Rajiyah, H. (General Electric Co., Astro-Space Div., Princeton NJ, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Publication Information
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)
Subject Category
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number
AAS PAPER 91-140
Distribution Limits
Public
Copyright
Other