AbstractFor a long time, EADS SPACE Transportation has been developing specific technologies and engineering capabilities in the field of re-entry. The first achievements were dedicated to ballistic missiles, but since recent years, these skills have found direct application into planetary exploration. Among these missions, EADS SPACE Transportation was involved in: Huygens program, in charge of the system activities and of the Thermal Protection System. Beagle 2, launched in June 2003 with ESA Mars Express orbiter, in charge of the Thermal Protection System. More recently, EADS SPACE Transportation was given the responsibility for the development of entry Thermal Protection System for the four NetLander probes, in the frame of the CNES Mars Premier program for which EADS SPACE Transportation has been selected by Alcatel Space for the development of the TPS. EADS SPACE Transportation has based its technical choices, on the Beagle 2 technologies well adapted to this application: the Norcoat Liège, a lightweight ablative material, for the external thermal protection of both the Back Cover and the Front Shield. A Nida/carbon layers sandwich for the Front Shield structure. For Programmatic point of view, the main objectives of this approach is to reduce the development risks and to increase the mission robustness in capitalizing on Beagle 2 experience and on a sound industrial basis, and to control the cost. For technical point of view, the major challenges of the Mars Netlander mission defined by the Prime is the mass saving and the design flexibility. Therefore, the materials have been optimised in line with these challenges: At the beginning of the phase B, a refined mechanical concurrent engineering has been performed for the Front Shield structure to optimize every part which are governed both by global requirements (volume allocation, overall stiffness and deformations) and by local ones (reinforcement zones under the sufM brackets, I/F with the Back Cover). Heat flux tests have been performed in the mission extreme conditions combining heat loads and aerodynamic shear stress to increase the material behaviour knowledge (ablation profiles, temperature prediction/results correlation) and at the end to reduce the sizing margins.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Entry system development for Mars Netlander mission


    Beteiligte:
    Plotard, P. (Autor:in) / Labaste, V. (Autor:in)

    Erschienen in:

    Acta Astronautica ; 55 , 3-9 ; 677-686


    Erscheinungsdatum :

    2003-01-01


    Format / Umfang :

    10 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





    Entry system development for Mars Netlander mission

    Plotard, P. | Online Contents | 2004


    Entry system development for Mars Netlander mission

    Plotard, P. / Labaste, V. / International Astronautical Federation et al. | British Library Conference Proceedings | 2004


    Navigation for the Mars PREMIER Netlander delivery

    Guinn, J. / Craig, D. / Carbonne, D. et al. | NTRS | 2003