Design Implications for Aerocapture Systems Placing Flagship-class Uranus Orbiters

Abstract

Aerocapture has the capability to deliver spacecraft to Ice Giant orbits while increasing on-orbit payload mass. Due to the aerodynamic forces and heat loads encountered during an aerocapture maneuver, the spacecraft must be contained by an entry vehicle, such as a typical rigid aeroshell used for planetary entry. This paper provides a preliminary design concept for an aerocapture system capable of delivering a flagship-class orbiter and planetary probe to Uranus orbit using heritage flight systems. The constraints of packaging large subsystems (radioisotope power systems, high gain antennas) and their effect on final aerocapture system design will be discussed. Mass properties will be presented for the system, with mass risks evaluated by margin policy implemented using standard mass properties control.