Abstract
The automation of a Mars aerobraking vehicle that uses reaction wheels for attitude and angular momentum control during atmospheric flythrough is investigated. In a previous study, single-axis control laws were developed for minimum onboard instrumentation to compensate for large variations in entry time and atmospheric density. Modifications of those control laws to provide two-axis control in high-fidelity simulations that include six degrees of freedom, nearly ideal reaction wheels, spherical harmonics, and oblate atmosphere are now tested. Preliminary results indicate that our approach may be highly practical for an autonomous aerobraking mission at Mars.
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