Abstract
Using a relatively general formulation procedure, the paper reviews complex interactions between deployment, attitude dynamics and flexural rigidity for configurations representing deployment of beam and tether type appendages. 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. Results suggest substantial influence of the flexibility, deployment velocity, initial conditions, and appendage orientation on the response, and under critical combinations of parameters the system can become unstable. The information has relevance to the design of control systems for: (i) the next generation of communication satellites; (ii) the Orbiter based experiments such as SAFE (Solar Array Flight Experiments), SCOLE (Structural Control Laboratory Experiment), STEP (Structural Technology Experiment Program), and-the NASA/CNR tethered subsatellite system; as well as (iii) the evolutionary transient and postconstruction operational phases of the proposed space station.
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