SmallSat Venus Aerocapture Mission Design and Performance Analysis

Interplanetary exploration can benefit from Aerocapture: a well-studied orbital insertion maneuver that utilizes a target planet’s atmosphere to decelerate into a closed orbit in a single pass. This maneuver can help reduce propellant mass and reduce travel time. However, Aerocapture has not been flight tested due to its high risk to costly missions. Recent innovations in small satellites have allowed for potential rideshare missions, which can help lower the risk of performing novel maneuvers in interplanetary missions. The planet Venus is of particular interest for Aerocapture due to the high atmospheric density, control challenges, and possibility of scientific exploration. To successfully perform a robust aerocapture maneuver, active guidance must be utilized. This paper will assess a pre-phase A analysis for a SmallSat Aerocapture rideshare mission to Venus. The Fully Numerical Predictor Aerocapture Guidance (FNPAG) Algorithm will be implemented for control. The design space for a SmallSat aerocapture mission to Venus will be assessed, comparing performance between two sphere cones, two steering algorithms, and two target science orbits. Nominal trajectory performance is assessed, and Monte Carlo analysis is performed to compare under uncertainty.