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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Mars Landing Vehicles: Descent and Ascent Propulsion Design Issues


    Contributors:

    Published in:

    Publication date :

    2022-02-04


    Type of media :

    Article/Chapter (Book)


    Type of material :

    No indication


    Language :

    English




    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