Numerical simulation is used to perform parametric analysis to assess the feasibility of aerocapture at Titan over arrival V of 0 16    km / s , vehicle lift-to-drag ratio of 0–1, and vehicle ballistic coefficient of 90 and 800    kg / m 2 . Aerodynamic forces, peak heat rate, and total heat load are evaluated. It is shown that aerocapture at Titan requires a lifting vehicle with a minimum lift-to-drag ratio of 0.2 and an arrival V of 5    km / s , an equivalent propulsive Δ V of about 4    km / s , which is higher than what is realistically possible. Results show that aerocapture requires different interplanetary trajectories from propulsive options, and aerocapture with a vehicle of lift-to-drag ratio of 0.3 enables an arrival V of 5    km / s and higher. The peak heat rate is well within the capability of the state-of-the-art technologies of thermal protection system materials. In addition, the vehicle can achieve an inclination change up to 20 deg via an aerocapture maneuver.


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    Titel :

    Feasibility Assessment of Aerocapture for Future Titan Orbiter Missions


    Beteiligte:
    Lu, Ye (Autor:in) / Saikia, Sarag J. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.09.2018




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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