Vehicle size and weight are driving cost factors in sending vehicles into space because the cost of launch is directly related to the payload mass being delivered. Vehicle size and weight have a larger impact on deep- space missions compared to sending a payload to low Earth orbit due to the extra fuel and supplies required to complete the longer duration mission. One area of study for possible vehicle volume or weight reduction is the thermal protection system (TPS) of a vehicle. Hot structures have been proposed as a TPS concept which can carry both primary structural loads and thermal loads. The use of hot structures on a Mars entry vehicle may be feasible and have potential volume and weight savings over the current state of the art ablative TPS technology. A preliminary trade study was performed on a mid lift-to-drag aeroshell Mars entry concept vehicle; comparing the weight and skin thickness of a vehicle using ablative TPS with a vehicle using hot structures. Independent thermal and structural analyses were performed to determine the minimum mass designs. The goal of this study was to determine if the use of hot structures was feasible and had potential for significant vehicle volume and weight savings over the current state of the art. This trade study found that use of a hot structures leads to a feasible alternative to ablative TPS technology, with potential 53% weight and 22% thickness (volume) saving benefits that could enable future missions.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Optimization of a Multifunctional Hot Structure Aeroshell for Mars Entry


    Beteiligte:
    S. L. Langston (Autor:in) / C. G. Lang (Autor:in) / K. Daryabeigi (Autor:in)

    Erscheinungsdatum :

    2018


    Format / Umfang :

    22 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Optimization of a Multifunctional Hot Structure Aeroshell for Mars Entry

    Langston, Sarah L. / Lang, Christopher G. / Daryabeigi, Kamran | NTRS | 2018


    Design of a Mars entry 'Aeroshell'

    Leonard, R. / Anderson, M. / Heard, W. | Tema Archiv | 1974


    Optimization of a Hot Structure Aeroshell and Nose Cap for Mars Atmospheric Entry

    Langston, Sarah / Lang, Christapher G. / Daryabeigi, Kamran et al. | AIAA | 2016


    Optimization of a Hot Structure Aeroshell and Nose Cap for Mars Atmospheric Entry

    S. L. Langston / C. G. Lang / J. A. Samareh et al. | NTIS | 2016


    Multiobjective Hypersonic Entry Aeroshell Shape Optimization

    Theisinger, John / Braun, Robert | AIAA | 2008