Adaptive Estimation of Nonlinear Spacecraft Attitude Dynamics with Time-Varying Moments of Inertia Using On-Board Sensors

For spacecraft conducting on-orbit operations, changes to the structure of the spacecraft are not uncommon. These planned or unanticipated changes in structural properties tightly couple with the spacecraft’s attitude dynamics and require estimation. For dynamic systems with time-varying parameters, multiple model adaptive estimation (MMAE) routines can be utilized to provide a probabilistic parameter and state estimate. This research applies MMAE routines that employ a parallel bank of unscented attitude filters to analytical models of spacecraft with time varying moments of inertia (MOI). The objective of this new application of adaptive estimation to the attitude determination problem is to estimate the time-varying MOI of the spacecraft and also to probabilistically classify spacecraft behavior. The results presented in this work use on-board three-axis magnetometers and gyroscopes for measurements and investigate the extension of sensor boom. This work lays the foundation for future research using ground-based measurements to estimate time-varying MOI and spacecraft behavior to further enhance the toolbox of the space situational awareness mission.

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