Critical Evaluation of the Lunar Data Center Concept: Structural Failure from Physical, Economic, Environmental, and Legal Perspectives

In response to the escalating electrical power and cooling crisis driven by hyperscale artificial intelligence (AI) data centers, speculative proposals have emerged advocating the offshoring of compute infrastructure to the lunar surface ("Lunar Data Centers"). Proponents routinely invoke the perceived availability of "unlimited solar energy" and "free cryogenic vacuum cooling" in Permanently Shadowed Regions (PSRs). This monograph conducts a rigorous, multi-disciplinary systems engineering evaluation across four foundational domains—thermodynamics, materials tribology and metallurgy, astro-economics and communications, and planetary environmental law—proving that the Lunar Data Center concept suffers from simultaneous, insurmountable structural failures. First, at the thermodynamic layer, because a hard vacuum eliminates conductive and convective heat transfer, heat rejection is governed exclusively by the Stefan-Boltzmann radiation law (Qrad ∝ ε σ A T⁴). Rejecting 1 MW of server thermal dissipation requires approximately 1,200 m² (~100 metric tons) of deployable radiator infrastructure, imposing a 10:1 cooling-to-compute mass penalty over the ~10 metric ton compute core itself. Second, at the materials layer, electrostatic adhesion of sharp lunar regolith (Mohs hardness 6–8) induces severe three-body abrasive wear, while a mere 1 mm dust coating degrades radiator solar absorptivity (αₛ) by 50%, inverting the cooling array into a net solar thermal heater. Concurrently, diurnal thermal cycling between +127°C and -196°C (Δ T ≈ 300 K) drives lead-free SAC305 (Sn-3.0Ag-0.5Cu) solder joints below their -100°C Ductile-to-Brittle Transition (DBT) into vitrified cleavage, causing Coffin-Manson fatigue fracture within 10–20 lunar cycles (1–1.5 Earth years). Third, at the economic and operational layer, surviving the 14-day (336-hour) lunar night requires 1,680 metric tons of battery mass per 1 MW, while Tsiolkovsky Δ v constraints reduce Falcon Heavy payload capacity from 63.8 metric tons in Low Earth Orbit (LEO) to just 5–7 metric tons soft-landed on the Moon. Paired with an absolute 2.5-second Earth-Moon round-trip latency and radiation-induced Single Event Upsets (SEUs), lunar hardware instantaneously becomes an unmaintainable Stranded Asset. Fourth, executing ~1,000 rocket launches per year injects black carbon and alumina (Al₂O₃) into the stratosphere—depleting stratospheric ozone by up to 6%—accelerates LEO Kessler Syndrome, and turns unweathered lunar PSRs into permanent electronic waste (E-waste) dumps in violation of the 1967 Outer Space Treaty. We conclude by formulating a four-pillar roadmap for returning from "Space Fantasy" to cold-eyed Terrestrial Systems Engineering: (1) radical semiconductor power efficiency improvements, (2) advanced liquid immersion cooling, (3) municipal district heating waste-heat reuse, and (4) autonomous, decentralized, seismically resilient terrestrial infrastructure.