Thermal ageing of polymer-matrix composite materials of any long-life spacecraft in LEO involves evolution of mechanical, thermophysical and morphological properties, especially if the structure operates under external mechanical stress like bending. Behavior of KMU-4l carbon/epoxy composite material under combined effect of thermal profiles and static mechanical loading has been studied in a simulated LEO space environment. Thermal cycling was performed on specimens under bending stress reaching 30.4 % of the material ultimate strength. Specimens subjected to combined thermal and mechanical fatigue were examined in a series of 4 intermediate points with a maximum of 120 cycles. The DMTA technique has been employed to follow the global thermomechanical response of KMU-4l composite. The degradation produced was detected by moisture diffusion analysis, the crack density was estimated at the edges of the specimens using a scanning electron microscope. Effects such as the temperature dependence of material properties and matrix post-curing phenomena are also discussed. The results are compared with the appropriate data obtained on specimens of KMU-4l exposed for up to 1501 days to LEO space environments onboard SALYUT and MIR space stations.


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    Titel :

    Predictive model for microcracking and mechanical properties of polymer-matrix composite materials for space applications


    Beteiligte:
    Issoupov, V. (Autor:in) / Viel-Inguimbert, V. (Autor:in) / Dinguirard, M. (Autor:in) / Startsev, O.V. (Autor:in) / Nikishin, E.F. (Autor:in)


    Erscheinungsdatum :

    2003


    Format / Umfang :

    6 Seiten, 12 Quellen



    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




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