Quantitative Assessment of Aerocapture and Applications to Future Solar System Exploration

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Quantitative Assessment of Aerocapture and Applications to Future Solar System Exploration

Girija, Athul Pradeepkumar / Saikia, Sarag J. / Longuski, James M. / Lu, Ye / Cutts, James A.

A quantitative and comparative assessment of the feasibility and mass benefit of using aerocapture at all atmosphere-bearing solar system destinations is presented, considering both lift and drag modulation control techniques. Aerocapture is shown to be feasible at Mars, Titan, and Venus with existing entry vehicles and flight-proven thermal protection system (TPS) materials, and requires no significant technology developments before use on a science mission. Aerocapture at Uranus and Neptune is viable with blunt-body aeroshells ( $L / D$ of 0.30–0.40) and Heatshield for Extreme Entry Environment Technology TPS for certain high arrival $V_{\infty}$ interplanetary trajectories. The mass benefit offered by aerocapture is compared to alternative orbit insertion techniques such as purely propulsive insertion and aerobraking. Aerobraking outperforms aerocapture for missions to Mars and Venus with arrival $V_{\infty}$ less than $6 km / s$ . For outer planet missions, aerocapture offers substantial mass benefit depending on the arrival $V_{\infty}$ , Titan (300–1700% more mass), Uranus (100–600%), and Neptune (80–400%), in addition to significant reduction in flight time. The study recommends a low-cost drag modulation aerocapture demonstration mission at Earth to establish flight heritage for aerocapture and lower the risk for future science missions.