| Abstract Scope |
Spacecraft in orbit are subjected to harsh conditions, including impacts from meteoroids and space debris, as well as extreme thermal fluctuations ranging from –150 °C in eclipse to 100 °C in sunlight. To ensure reliable operation, their structural materials must achieve a challenging balance of low density, low thermal expansion, high strength, and high toughness. Current spacecraft structures are therefore assembled using multiple alloys, each selected for specific properties; for example, aluminum 7000-series for lightweight components, Ti-6Al-4V for high specific strength, and Invar for its low thermal expansion and toughness. However, this multi-alloy strategy inevitably increases manufacturing complexity, cost, and assembly time. In this study, we propose an alternative approach using a cladding technique to overcome conventional property trade-offs. Specifically, high-strength, precipitation-hardened martensitic steel was clad with Invar, aiming to unify the required properties within a single integrated material system. |