The finite element method is applied to generate a linear mathematical model of a general flexible spacecraft in arbitrary orbits. Model order is reduced by a quasi-static approximation of the higher frequency characteristic modes. Stochastic models to approximate modeling errors are proposed. The models for parameter estimation are linear dynamical systems with unknown process noise. Algorithms for maximum likelihood parameter estimation which account for correlations between process and measurement noise are developed. Simulated measurements are used to verify the applicability of the maximum likelihood parameter estimation algorithms to the identification of flexible spacecraft. It is demonstrated that for the spacecraft used, all unknown parameters can be estimated from the simulated measurements simultaneously with the time histories of the system model states.
Maximum Likelihood Parameter Identification of Flexible Spacecraft
1987
272 pages
Report
Keine Angabe
Englisch
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