Human and robotic Mars missions often include plans for landing large payloads on the planet’s surface. Thus far, landing of payload of up to approximately 1 metric ton (MT) have been successful. Future human missions have suggested large 5 to 25 MT surface payloads may be needed. Therefore, large landing vehicles with an initial mass of up to 100 MT may be required. In this chapter, the future human payload missions are assessed, investigating the mission velocity changes (delta-V) values for deorbit, deceleration, landing and ascent. The initial masses of single and multi-stage Mars landing vehicles are computed. Issues related to vehicle mass factors and delivering the needed delta-V are discussed.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Mars Landing Vehicles: Descent and Ascent Propulsion Design Issues


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    04.02.2022


    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Mars Entry, Descent, Landing, and Ascent Systems Sensitivities to Landing Site and Atmospheric Dust

    Trent, Douglas / Thomas, Dan / Samareh, Jamshid A. et al. | AIAA | 2021


    Mars Entry, Descent, Landing, and Ascent Systems Sensitivities to Landing Site and Atmospheric Dust

    Douglas J Trent / Herbert D Thomas / Jamshid A Samareh et al. | NTRS




    Mars Entry, Descent, Landing, and Ascent Systems Sensitivities to Landing Site and Atmospheric Dust

    Douglas J Trent / Herbert D Thomas / Jamshid A Samareh et al. | NTRS