The current project investigated the feasibility of aerocapture at Jupiter, and the benefits in terms of payload mass fraction that could be achieved compared to traditional orbital insertion burns. A numerical simulation model has been set up, as well as an analytical formulation of the problem. The numerical verification of the analytical model showed that the analytical model still needs to be refined to produce accurate and useful results.
Thermal fluxes, a driving aspect of aerocapture, have been implemented by using correlation laws, as well as corrective terms, all retrieved from literature.
The aerocapture problem was numerically modeled and has been then optimized. However, the best trajectories provided a negative mass fraction benefit of −0.37 when compared to a traditional insertion burn. The best available mass fraction for the spacecraft's entry-unrelated subsystems was 0.44.
Therefore, apart from some niche applications, aerocapture at Jupiter can be considered unappealing at best in the near future.