Science
Project Helios Science
This section contains detailed descriptions of technologies from the book. We recommend reading after familiarizing yourself with the main storyline.
This is a feasibility study. All calculations are order-of-magnitude estimates and require detailed engineering work during the R&D phase.
Study Conclusion: Fundamental feasibility is confirmed. All necessary technologies exist or are at high readiness levels (TRL 4-9). Budget ($200-490B) and timeline (10-15 years) are comparable to other human megaprojects.
Quick Start
1. Project in 5 Minutes (~9 min)
Complete project overview: Swarm of 1.1 billion mirrors → ~102 PW solar energy → ~18 PW on Earth (~800× global consumption). Four deployment phases, key technologies, budget $200-490B.
2. Roadmap (~26 min)
Timeline of 4 phases: R&D (years 1-4) → Moon (4-6) → Mercury (6-10) → Swarm. Critical path: blitz factory assembly in 7 days, first MD in 6 months. Year 1: 47 TW to Earth, year 3: 1000 Mass Drivers.
3. Budget (~26 min)
Three scenarios: $200B (optimistic), $355B (baseline), $490B (conservative). Comparison with Apollo ($280B), ISS ($150-250B). Analysis of potential underestimates: AI, infrastructure, contingencies.
4. Why Mercury? (~6 min)
Why Mercury instead of Moon or Mars? Comparison by solar flux (10 vs 1.4 kW/m²), Mass Driver challenges, decommissioning of retired mirrors. Tradeoff “speed vs risk”: Moon as backup path.
5. Technologies and Sources (~22 min)
TRL analysis of all project technologies + complete bibliography. Electromagnetic launch, lights-out factories, autonomous mining, NaS batteries, MRE electrolysis, microwave power transmission.
6. Swarm Mirrors (~22 min)
Design of frameless 100×100 m mirror (116 kg). Project energy: cascade efficiency 18%, power on Earth ~18 PW. Attitude control, thermal balance, degradation (8-12 year lifespan).
7. LSP Stations (~11 min)
Why lunar LSP stations instead of orbital Hub (18% vs 10% efficiency, no 7,900 km² radiator problem). Placement of 40 stations on lunar limbs, microwave transmission at 230 W/m². Global rectenna network.
8. Production (~28 min)
Two centers: Mercury (mirrors, self-replication 1→~1650 factories) and Moon (testbed + LSP). F-M (~350 mirrors/day), F-R (robots, domes, equipment). Critical resources: iridium, carbon, “Vitamins”.
9. Risks and Limitations
Honest analysis: 5 solved critical risks, 6 open technical problems (mirror degradation, iridium deficit). What can go wrong and how it’s accounted for.
Additional Topics
Moon
Triple role: technology proving ground + LSP stations for energy reception + backup site (less risky alternative to Mercury). 1.3 sec communication delay allows near-real-time operator control.
Mars (perspective)
Terraforming as a side project after main completion: magnetic shield (100-1000 satellites, 100 GW), polar heating (500 TW, 2-3 months), greenhouse effect. First lake by 2072, breathable atmosphere in 150-300 years. Consumes only 15% of Swarm power.
Delivery
Earth → Moon → Mercury logistics: ~50-100 launches over ~10 years (thanks to 99.998% localization), 15-30 launches in peak year. Cost $8-20B. Synergy with Artemis, Chang’e, ILRS programs.
First Factory Assembly (Bootstrap)
Unique project phase: Gen-1 robots assemble first factory from 100% imported materials. Critical checkpoint: energy autonomy within 12-24 hours. Three scenarios: 7/11-16/22-32 days.
Reference
Glossary
25+ project terms: Dyson Swarm, power beam, “Vitamins”, self-replication, electrochromics, Mass Driver, NaS battery, phased array, Gen-1/Gen-2.
Physical Constants
Reference tables for calculations: solar constant, planetary parameters, regolith composition, material properties, mirror and Mass Driver characteristics.