Abstract
Complex interactions between deployment, attitude dynamics and flexural rigidity are reviewed using a rather general formulation applicable to a large class of space platforms with flexible, extensible members. The governing nonlinear, nonautonomous and coupled hybrid set of equations are extremely difficult to solve even with the help of a computer, not to mention the cost involved. Effectiveness of the versatile formulation is demonstrated through its application to several dynamical situations of contemporary interest involving beam type appendages. Both transient as well as post-deployment phases are considered. Results suggest significant influence of flexibility, inertia, deployment time history and orbital parameters on the system stability. The presence of free molecular and solar radiation induced environmental forces may further accentuate this tendency. The information has relevance to the design of control systems for the next generation of communications satellites with large solar panels; the Orbiter based experiments such as SAFE, COFS, NASA/CNR tethered subsatellite system, etc.; as well as constructional and operational phases of the proposed space station.
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