Source Review: Coutts and Sowers 2025 (Sage Journals, VOI for lunar ice)

Summary

Claim 1: Starship LEO cost $30-$300/kg

Source content (paraphrased; original is paywalled, this is from extract's "key-anchors-quoted-in-secondary-sources" block): Starship LEO launch cost used as L_p assumption is $100/kg base case; $300/kg pessimistic (10 reuses); $30/kg optimistic (100+ reuses). Verdict: Consistent Why: Matches q1's optimistic-to-pessimistic range. My Earth-imports-only gear-ratio amplification uses these figures correctly.

Claim 2: $500/kg lunar surface propellant target

Quote (from secondary summary): "The price ULA is willing to pay on the surface of the Moon is $500/kg for 1100 mT of propellant per year." Verdict: Consistent Why: Used as the maturity-era market clearing price anchor in q2.c10. My aggressive-ISRU production range ($300-2000/kg across eras) spans this.

Claim 3: 1100 mT/yr propellant demand

Quote: "1100 mT of propellant per year on the lunar surface" Verdict: Novel supporting Why: Provides a demand-side anchor for q6 (orbital demand). My q2 calc doesn't use this directly but it's relevant to whether the ISRU operation can amortize fixed costs. Captured for q6 flagging.

Claim 4: VOI methodology — lunar propellant has positive NPV under uncertainty

Quote (paraphrased): "Lunar propellant could yield positive net present value even under unfavorable conditions, making ground-based exploration economically justified." Verdict: Merits investigation Why: Coutts-Sowers report positive NPV; my q2 calc shows lunar-to-LEO chemical is 9-17× more expensive than terrestrial. The reconciliation: Coutts-Sowers's "lunar propellant" is delivered to cislunar destinations where Γ is O(1), not to LEO where Γ ≈ 14. Flag for q8 synthesis.

Anti-hallucination check

The paper is paywalled and the extract relies on Sage Journals abstract + secondary citations. All quotes above are from the secondary search summaries; the primary numerical figures (cost ranges, propellant demand) should be re-verified against a direct read of the paper if it becomes accessible. Flagged in the extract's "limitations" section.

Coutts and Sowers 2025 — VOI framework for lunar ice + cost anchors

Paywalled paper. Extract built from abstract, Sage Journals metadata, and contemporaneous secondary reporting. Critical for q2 because Sowers is the original ULA price-setter on lunar propellant ($500/kg surface price) and Coutts-Sowers update those anchors for 2025.

key-anchors-quoted-in-secondary-sources

• Starship LEO launch cost (used as L_p assumption): $100/kg base case; $300/kg pessimistic (10 reuses); $30/kg optimistic (100+ reuses). This is the Starship-cost input to their lunar economics model.
• Lunar surface propellant target price: $500/kg (the ULA Sowers 2016 anchor, carried forward to 2025).
• Annual demand assumption: 1100 mT/yr of propellant on lunar surface; 100 mT/yr to support ascent vehicles (NASA-style demand profile).
• Conclusion (paper-level): Lunar propellant business case is robust under uncertainty — positive NPV across most scenarios in their Monte Carlo. Information value of pre-extraction prospecting is high.

relevance-to-q2

The lunar-surface-to-LEO cost is NOT directly stated by Coutts-Sowers. What they provide:

• Anchor for L_p (Starship Earth-to-LEO cost): $30–300/kg matches q1's optimistic-mid range.
• Anchor for lunar-surface propellant cost: $500/kg. This is the price ULA was willing to pay buyers in 2016 dollars, carried forward.
• Implicit lunar-ascent vehicle architecture: chemical hydrolox lunar lander, refueled from ISRU propellant.

derived-back-of-envelope-from-anchors

If lunar-surface propellant is $500/kg and lunar-ascent ΔV is ~1.87 km/s to LLO (hydrolox Isp 450 s gives propellant mass fraction ~0.34 of takeoff mass) — then propellant cost alone is ~$170/kg of payload mass, before any hardware amortization, ops, or return-to-Earth maneuver. This is just one term in the full ascent cost stack.

limitations

• Paywalled; primary numbers extracted from secondary sources
• Architectural assumptions buried; the gear-ratio breakdown is not surfaced in the abstract
• 2025 publication uses 2025-era Starship optimism that has not yet been fully validated by Starship operations