A feasibility study was conducted to investigate the potential performance advantages of Supersonic Retro-Propulsion in support of future high-mass Mars robotic landing missions. A notional reference architecture for a potential future Mars Sample Return formed the basis for assuming a 4.7 m diameter SRP entry vehicle containing the Mars Ascent Vehicle element. Configuration analysis was conducted to ensure that the payload and required SRP components (including engines and propellant) fit within in the capsule volume. Optimized trajectory analysis highlighted several key performance sensitivities of SRP for ballistic coefficients of 150, 300, and 450 kg/m2. These results indicated a broad SRP ignition envelope (1-4 km altitude, 300-750 m/s velocity), as well as relatively small propellant mass fraction sensitivities to SRP thrust/weight, landing site elevation, and the application of a 4-g entry deceleration constraint (relevant for future crewed mission trajectories). Finally, mass-sizing was performed to assess sensitivities to ballistic coefficient and entry velocity, and showcased the ability of the SRP system to land payload masses on the order of twice that of MSL.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Supersonic Retro-Propulsion for Future High-Mass Robotic Mars Lander Missions


    Beteiligte:
    Whetsel, Charles (Autor:in) / Wolf, Aron (Autor:in) / Lobbia, Marcus (Autor:in)

    Erscheinungsdatum :

    2017-06-05


    Medientyp :

    Preprint


    Format :

    Keine Angabe


    Sprache :

    Englisch



    Supersonic retro-propulsion for future high-mass robotic Mars lander missions

    Whetsel, Charles / Wolf, Aron / Lobbia, Marcus | NTRS | 2017



    Development of Supersonic Retro-Propulsion for Future Mars Entry, Descent, and Landing Systems

    Edquist, Karl / Korzun, Ashley / Studak, Joseph et al. | AIAA | 2010


    Development of Supersonic Retro-Propulsion for Future Mars Entry, Descent, and Landing Systems

    Edquist, Karl T. / Dyakonov, Artem A. / Shidner, Jeremy D. et al. | NTRS | 2010


    A Mapping Balloon for Future Robotic and Human Lander Missions to Mars

    Totzek, K. / Zylka, A. / Schafer, B. et al. | British Library Conference Proceedings | 2006