Many concepts for future robotic Mars lander missions require landing heavier payloads than those landed to date. Mars lander architectures to date have relied on a parachute to help slow the lander; however the effectiveness of a parachute in the thin Martian atmosphere is diminished with heavier payloads unless the diameter of the parachute is increased or it is deployed at a higher Mach number, both of which are significant technical challenges. In addition the parachute can be successfully deployed only within a specific Mach number and dynamic pressure range. Targeting the entry trajectory to hit this “Mach-Q box” imposes constraints on the entry ballistic coefficient, limiting it to ~ 150-200 kg/m^2. Eliminating the parachute from the design requires descent engine ignition at supersonic speeds (Supersonic Retropropulsion, or SRP). SRP increases the propellant requirement, but also allows entry ballistic coefficients of ~600 kg/m^2 or more, with the consequence of significantly increased entry mass and landed payload mass.


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    Titel :

    Supersonic Retropropulsion on Robotic Mars Landers: Selected Design Trades


    Beteiligte:
    Lorenz, Christopher G. (Autor:in) / Putnam, Zachary R. (Autor:in) / Nakazono, Barry (Autor:in) / McCann, John (Autor:in) / Lobbia, Marcus (Autor:in) / Benito, Joel (Autor:in) / Strauss, William (Autor:in) / Noyes, Connor (Autor:in) / Wolf, Aron A. (Autor:in)

    Erscheinungsdatum :

    19.08.2018


    Medientyp :

    Preprint


    Format :

    Keine Angabe


    Sprache :

    Englisch



    Supersonic Retropropulsion on Robotic Mars Landers: Selected Design Trades

    Lorenz, Christopher / Putnam, Zachary / McCann, John et al. | NTRS | 2018


    Supersonic Retropropulsion (SRP) for Robotic Mars Landers

    Wolf, Aron / Manning, Rob / Benito, Joel et al. | NTRS | 2016




    High Ballistic Coefficient Mars EDL with Supersonic Retropropulsion

    Noyes, Connor / Wolf, Aron / Benito, Joel | NTRS | 2017