The protection of a reusable transfer vehicle from space debris is discussed. The results of a debris protection analysis are given. It was concluded that a shielding thickness of 0.62mm (24 mils) equivalent aluminum was needed when using a good double wall design. An additional 0.43 mm (18 mils) of shielding was needed during on-orbit storage time between flights.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Space debris protection for a reusable orbital transfer vehicle


    Contributors:
    Davis, E. E. (author) / Sperber, R. (author)


    Publication date :

    1985-03-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Meteoroid/orbital debris implications to a reusable launch vehicle thermal protection system

    Robinson, Jennifer / Nolen, Angela / Wittman, David et al. | AIAA | 1995





    Reusable Orbital Transfer Vehicle Spacelift Concepts Study Results

    Feuchter, C. A. / Grobman, J. H. / University of New Mexico; School of Engineering; Institute for Space and Nuclear Power Studies | British Library Conference Proceedings | 1997