On the Dynamics and Control of Flexible Orbiting Systems: An Approach with Application

by V. J. Modi, Univ of British Columbia, Vancouver, BC, Canada,
A. Suleman, Univ of British Columbia, Vancouver, BC, Canada,



Document Type: Proceeding Paper

Part of: Engineering, Construction, and Operations in Space IV

Abstract:

A relatively general formulation for studying the dynamics and control of an arbitrary spacecraft, with interconnected flexible, deployable and articulating structural members, is reviewed which accounts for thermal deflection, transient system properties, shift in the center of mass, shear deformations, rotary inertias and geometric nonlinearities. A rather self-contained, comprehensive, numerical algorithm using system as well as component modes follows which is applicable to a large class of spacecraft configurations of contemporary and future interests. Versatility of the general formulation has been assessed so far through its application to Japan's Space Flyer Unit (SFU); Canadian Mobile Servicing System (MSS); and the recently launched (August 1992) Indian communications satellite INSAT-II. Here the focus is on the dynamics and control studies aimed at the evolving Space Station Freedom.



Subject Headings: Orbits | Structural control | Thermal properties | Structural dynamics | Control systems | Structural deflection | Shear deformation | Space stations | Japan | Asia

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