Abstract
Station-keeping of a small spacecraft is studied and a solution based on resilient periodic state-feedback control laws is proposed. Linearized equations of the relative motion of the satellite near an eccentric reference orbit are derived in the presence of the second zonal gravitational harmonic J2 and atmospheric drag perturbations. After a discretization of the model, a resilient H2 state-feedback control law is computed by a linear matrix inequality-based algorithm. Illustrative nonlinear simulations show the efficiency of the approach.
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