Characterization of epoxy-nanoparticle composites exposed to gamma & UV radiation for aerospace applications

The present work lies in the framework of designing polymeric fibre reinforced materials to be used in nanosatellite structures (CubeSat). In the design of any structural system for a space mission the balance between mass, stiffness and strength must be taken into account, also the used materials have to be appropriated for the space environmental conditions. The CubeSat are exposed to high radiation levels (because of the sun irradiance), and so, the accurate determination of the thermal and radiation properties are a key issue for the materials design used in such applications. This work reports the thermal and radiation performance of a biphasic epoxy resin system incorporating two types of ceramic nanoparticles: zinc oxide and graphene, chosen as potential fillers to improve the thermal properties of the epoxy system. Materials are exposed to Gamma and UV radiation at rates of 1 kGy and 10kGy and characterized after exposure. Different characterization techniques (Thermogravimetric analysis, Dynamic Mechanical Analysis, X-ray diffraction, Optical Microscopy, Scanning Electron Microscopy and Colorimetry) are performed to determine thermal properties and possible material degradation after radiation exposure. The influence of the different nano-filler in the thermal and radiation response of the epoxy system are discussed. Thermal properties found are also added to the Finite Element Analysis of a CubeSat composite structure to estimate more accurately its performance under the thermal load and environmental conditions during satellite life cycle.