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.

    Highlights A Flagship-class Uranus Orbiter and Probe mission using aerocapture is presented. The mission uses a cost-effective Falcon Heavy launcher and a heritage entry system. The mission delivers a 1400 kg orbiter and a 300 kg probe to Uranus within 8 years. The concept enables a 10-year tour at Uranus to explore the planet and its moons.


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    Titel :

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


    Beteiligte:

    Erschienen in:

    Acta Astronautica ; 202 ; 104-118


    Erscheinungsdatum :

    2022-10-04


    Format / Umfang :

    15 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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