Nonlinear Spacecraft Dynamics with a Flexible Appendage, Damping, and Moving Internal Submasses

We study the attitude dynamics of a single-body spacecraft that is perturbed by the motion of small oscillating submasses, a small e exible appendage constrained to undergo only torsional vibration, and a rotor immersed in a viscous e uid. We are interested in the chaotic dynamics that can occur for certain sets of the physical parameter values of the spacecraft when energy dissipation acts to drive the body from minor to major axis spin. Energy dissipation, which is present in all spacecraft systems and is the mechanism that drives the minor to major axis transition, is implemented via the rotor. We not only obtain an analytical test for chaos in terms of satellite parametersusing Melnikov’ s method, but wealso use extensivenumericalsimulation to check the rangeof validity of the Melnikov result.

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