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

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

Sep 2003

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2003esasp.540..407i&link_type=abstract

In: Proceedings of the 9th International Symposium on Materials in a Space Environment, 16-20 June 2003, Noordwijk, The Netherla

Mathematics

Logic

Space Environment, Materials, Modelling

Scientific paper

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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