A Flagship-class Uranus Orbiter and Probe mission concept using aerocapture

Abstract

The conceptual design for a Flagship-class Uranus Orbiter and Probe (UOP) mission using aerocapture is presented. Uranus is historically the least studied destination for aerocapture, primarily attributed to the lack of an engineering-level atmosphere model until UranusGRAM was released by NASA in 2021. The present study is the first detailed end-to-end study of a Uranus aerocapture mission concept taking into account constraints arising from launch vehicle performance, interplanetary trajectory, aerocapture vehicle design, thermal protection system, and probe delivery. The mission concept uses a Falcon Heavy Expendable launcher and a high-energy, fast-arrival V∞ Earth–Earth–Jupiter–Uranus (EEJU) gravity assist trajectory to deliver a 1400 kg orbiter and a 300 kg entry probe to Uranus. The aerocapture vehicle is a derivative of the Mars Science Laboratory entry system with extensive flight heritage, and uses the state-of-the-art HEEET thermal protection system. Compared to the current baseline UOP mission using conventional propulsive orbit insertion with a 13-year flight time and 5-year orbital mission at Uranus, the proposed 8-year aerocapture mission concept enables a 10-year orbital mission at Uranus within the budgetary and schedule constraints of a Flagship-class mission.