Tracking validation status of LLM predictions and specifications against real data, experiments, and expert review. Claims are validated, refuted, or marked as needing further investigation based on evidence.
Sunshield reduces 204kW solar input to 40-135W. Two-stage active cooling at 10-20kW achieves ZBO for full tank farm. Less than 1% of 2.5-3.25MW station power.
Pure microgravity smelting not viable at industrial scale. Rotating arm (~50m, 1.4 RPM) provides 0.1g for smelting. Mass 340-430k kg. Reduces risk from TRL 2-3 to TRL 3-4.
NEA median $3,333/kg vs Lunar $4,845/kg. P(NEA cheaper)=90.4%. EP payload fraction 83% vs chemical 57% is the dominant driver.
Magnetically shielded Hall thrusters (HERMeS) demonstrated 3,570 hours with zero channel wall erosion. Inner front pole cover is the new life limiter (not walls). NEXT ion thruster exceeded 50,000 hours in ground testing. 50,000+ hour Hall thruster lifetime is credible with magnetic shielding, supported by AEPS/Gateway flight program at TRL 8-9.
At 10km spacing with active station-keeping, collision probability is 3.2 x 10^-10 per unit per year, well below threshold
100ms at 1M scale is ambitious but theoretically achievable with optimal hierarchical design and edge computing
Production estimates accurate; major constraint is competing demand from semiconductor industry
Industry experience confirms 10-100 microsecond range for operational optical links; sub-microsecond not achievable with current technology
Literature suggests wide range of 0.2-2% depending on encapsulation and composition; more in-situ data needed
ISS solar array power output has declined 2.5% annually on average over 25 years of operation, consistent with predictions