Baseline micrometeoroid and orbital debris fluence estimates for spacecraft in low Earth orbit (LEO) are provided. For these calculations, an orbit similar to that of the International Space Station (ISS) is used.


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    Space Station JEM design for micrometeoroid and orbital debris protection

    Shiraki, K. et al. | British Library Online Contents | 1996


    Micrometeoroid and Orbital Debris Hazard Considerations for Space Station-Related EVA

    Cour-Palais, B. G. / Hodgson, E. W. / Rayfield, J. et al. | SAE Technical Papers | 1993


    Space Station JEM design for micrometeoroid and orbital debris protection

    Shiraki, K. et al. / European Space Agency / Centre national d'etudes spatiales et al. | British Library Conference Proceedings | 1996



    PROTECTION OF SPACE VEHICLES FROM MICROMETEOROID/ORBITAL DEBRIS (MMOD) DAMAGES

    Barr, S. / European Space Agency | British Library Conference Proceedings | 2007