Abstract
The problem of errant rocket burns in low Earth orbit is of growing interest, especially in the area of safety analysis of nuclear powered spacecraft. The development of stochastic Hill's equations provides a rigorous mathematical tool for the study of such errant rocket maneuvers. These equations are analyzed within the context of a theory of linear dynamical systems driven by a random white noise. It is established that the trajectories of an errant rocket are realizations of a Gauss-Markov process, whose mean vector is given by the solution of a deterministic rocket problem. The time-dependent covariance matrix of the process is derived in an explicit form.
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Ostoja-Starzewski, M., Longuski, J.M. Stochastic Hill's equations for the study of errant rocket burns in orbit. Celestial Mech Dyn Astr 54, 295–303 (1992). https://doi.org/10.1007/BF00049143
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DOI: https://doi.org/10.1007/BF00049143