Speakers
Description
The ESA funded project (Contract No. 4000147841/25/NL/KML) aims to design, manufacture, and validate innovative lightweight radiation shielding materials for the protection of electronic components onboard spacecraft. Reducing mass while maintaining effective shielding performance remains a key challenge for future space systems.
A promising strategy investigated in this work is the graded Z shielding concept, which combines materials with low and high atomic numbers to optimize particle attenuation across a broad radiation spectrum. Additive manufacturing approaches, and in particular cold spray deposition combined with ceramic or metallic filled epoxy resin layers, enable precise control of material composition, architecture, and interface properties. Multilayer composite systems based on W, Bi₂O₃, and B₄C, integrated with particle loaded polymer matrices, are being developed to tailor shielding performance for specific orbital radiation environments and localized spacecraft protection.
In addition to radiation attenuation, these composite materials must withstand harsh space environments, including UV exposure, particle irradiation, extreme thermal cycling, atomic oxygen erosion, and humidity. The incorporation of ceramic or metallic fillers within the epoxy matrix is expected to enhance thermal stability, mechanical robustness, and resistance to cracking or delamination, while maintaining manufacturability and adhesion between layers. To assess these aspects, a comprehensive experimental campaign is being conducted, including radiation ageing, thermal cycling, outgassing analysis, tensile strength and adhesion testing, as well as thermal conductivity measurements.
The primary objective of this activity is to achieve Technology Readiness Level (TRL) 6 for a radiation shielding solution applicable to LEO, MEO, and GEO missions. This presentation will introduce the multilayer modeling and design approach, describe the first manufacturing trials of composite multilayers using cold spray deposition and charged epoxy application, and report initial microstructural and mechanical characterization results. Finally, the forthcoming work plan will be outlined, including radiation shielding efficiency and durability testing at both coupon and engineering model levels.