Feasibility Study of Aerocapture at Mars with an Innovative Deployable Heat Shield
Giorgio Isoletta (1), Michele Grassi (1), Elena Fantino (2), David de, la Torre Sangr\`a (3), Jes\'us Pel\'aez \'Alvarez (4) ((1) University of, Naples "Federico II", (2) Khalifa University of Science, Technology, (3), Polytechnic University of Catalonia (UPC)

TL;DR
This study explores the feasibility of using an innovative deployable heat shield for aerocapture at Mars, analyzing uncertainties in atmospheric density and navigation errors to identify viable orbital insertion solutions.
Contribution
It introduces a novel deployable drag device and assesses its effectiveness under various uncertainties through parametric analysis and real mission scenario simulations.
Findings
Viable aerocapture solutions exist despite high uncertainties.
Atmospheric density and ballistic coefficient uncertainties significantly affect success.
Deployable heat shield can enable resource-efficient Mars orbit insertion.
Abstract
Performing orbital insertion around Mars using aerocapture instead of a propulsive orbit insertion manoeuvre allows to save resources and/or increase the payload mass fraction. Aerocapture has never been employed to date because of the high uncertainties in the parameters from which it depends, mainly related to atmospheric density modeling and navigation errors. The purpose of this work is to investigate the feasibility of aerocapture at Mars with an innovative deployable drag device, whose aperture can be modulated in flight, and assess the effects of the main uncertainties on the success of the manoeuvre. This paper starts with the presentation of a parametric bi-dimensional analysis of the effectiveness of aerocapture, for which a wide range of uncertainty levels in the atmospheric density and the ballistic coefficient are considered. Then, an application to a real mission scenario…
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