Earth for Life. Space for Heavy Lifting. 2.0

A technical statement for the System State Atlas

Proposed principle: protect Earth’s living systems and expand useful space infrastructure only where a complete, inspectable comparison supports the change. Develop production near its actual point of use; keep the costs, wastes, hazards and responsibilities visible across the entire supply chain.

This revises the original direction into a testable program. It does not assume that moving a process above the atmosphere makes it cleaner. It does not make the protection of Earth dependent on a future elevator, lunar mine or orbital factory. Conservation, efficient terrestrial industry and low-impact energy remain immediate work. Off-world infrastructure earns its role through measured performance against those alternatives.

The proposal belongs to Unified State. The data, constants and technical results cited below come from identified scientific and institutional sources. Their use does not imply institutional endorsement of the proposal, USST or System State.

1. Define the service before choosing the location

The unit of comparison must be a delivered service: for example, one kilogram of qualified oxygen available at a specified lunar depot, one certified replacement part delivered to an orbital station, or one megawatt-hour supplied to a terrestrial grid with an identified reliability profile. A kilogram of lunar regolith is not equivalent to a kilogram of finished steel. An intermittent watt at a panel is not a reliable watt at a customer.

For each candidate, publish destination, useful output, quality, throughput, lifetime, availability, repair assumptions, and the Earth-based counterfactual. Compare at least three paths: avoid or reduce demand; improve or recycle the terrestrial supply; manufacture or recover material off Earth. In-space use and return-to-Earth markets need separate cases because their transport requirements differ.

The first promising question is consequently narrow: which locally used space products can displace more imported equipment, feedstock and consumables than their complete production system requires? That question can be tested before proposing relocation of whole terrestrial industries.

2. Begin with demonstrated mechanisms—and retain their limits

MOXIE produced a reported 122 grams of oxygen across its Mars mission, reaching 12 grams per hour at 98% purity or better. This demonstrates extraction from the Martian atmosphere in a small instrument; it does not establish an industrial propellant plant, liquefaction chain or economic advantage. NASA’s MOXIE completion record

ESA’s technology demonstrator printed its first complete metal shape aboard the International Space Station in August 2024. Returned samples were subsequently examined on Earth. This supports a real manufacturing capability in microgravity, while qualification, maintainability and production economics remain distinct questions. ESA’s first metal-part record, ESA’s examination of the returned part

Failures are equally useful evidence. NASA’s 2025 In-Space Manufacturing Portfolio Plan reports that Refabricator did not complete its intended recycling demonstration and returned to Earth; filament breakage and foreign-object debris were identified as likely factors. A development objective must not become a demonstrated closed loop merely through repetition in a proposal. NASA portfolio plan, 20250004020

The near-term program should therefore favor bounded demonstrations: feedstock qualification, repair, recycling yield, autonomous inspection, metrology, thermal control and verified part performance. Bulk lunar processing, large depots and orbital shipyards remain systems to demonstrate, with their resource and environmental accounting attached.

3. Close the mass balance

For an initial screening model, let annual useful output be q kg/year, service life L years, imported consumables c kg per kilogram of product, and imported plant, spares and replacements total M_fixed. Compare delivery to the same destination:

Earth-supplied product mass = q L
Local-production imported mass = M_fixed + c q L
Net imported mass avoided = (1 − c) q L − M_fixed
Mass break-even time = M_fixed / [(1 − c) q], when c < 1

These are accounting identities under the stated assumptions, not forecasts. A scenario with q = 10,000 kg/year, L = 10 years, c = 0.10 and M_fixed = 20,000 kg avoids 70,000 kg of imports over the assumed life and reaches mass break-even after 2.22 years. The calculation becomes unfavorable if availability, yield or service life falls far enough, or if replacement and logistics mass is omitted.

Mass break-even is not automatically cost, energy or ecological break-even. Equipment, electrical power, transport stages, storage losses, excavation, rejected batches, packaging, shielding and disposal must appear in the detailed model. A tonne delivered to low Earth orbit and a tonne delivered to a lunar surface site carry different burdens.

An operating plant should report input–output closure: imported feedstock + locally acquired feedstock + stock withdrawals = useful product + waste + emissions + stock growth. Unexplained residuals are measurement gaps; they are not circularity.

4. Launch is a physical burden, not a free boundary crossing

A simplified mechanical-energy comparison illustrates the scale. For Earth’s gravitational parameter μ, starting radius R, final circular-orbit radius r and equatorial surface rotation ω, the increase in payload mechanical energy is:

Δe = μ/R − μ/(2r) − (ωR)²/2

Using μ = 398600.435507 km³/s² from JPL, R = 6378.137 km as the declared reference radius, r = R + 400 km and ω = 7.292115×10⁻⁵ rad/s, the result is approximately 33.0 MJ/kg, or 9.16 kWh/kg. The circular speed is approximately 7.669 km/s. These are a two-body payload energy difference and orbital speed, not fuel consumption, price, usable rocket efficiency or a complete launch trajectory. Drag, gravity losses, engines, stages and propellant manufacture add major requirements; Earth rotation depends on site and launch direction. JPL astrodynamic parameters

The ideal rocket relation Δv = v_e ln(m₀/m_f) explains why delivered mass is sensitive to mission velocity requirements and propulsion assumptions. It cannot by itself determine emissions or the full lifecycle burden.

Atmospheric accounting must identify propellant, engine, altitude, soot, alumina, chlorine-bearing species, nitrogen oxides, water and reentry products rather than reducing every effect to launch CO₂. Peer-reviewed inventories and atmospheric modeling show why injection altitude and species matter. Such studies model particular traffic and emission scenarios; they do not establish that every projected launch system has the same impact. Brown et al., 2024 launch-emissions inventory, Maloney et al., 2022 black-carbon modeling

Cleaner propellants, reusable vehicles and electric transfer can each change parts of the account. None should receive an unmeasured blanket designation of zero impact.

5. Energy collection and heat rejection both set the architecture

For a first-order solar estimate, use a reference irradiance S₀ ≈ 1361 W/m² at 1 au and S(r) = S₀/r², with r in au. The reference is a measured scale, not an immutable solar constant or a prediction of local illumination. At 1.524 au the estimate is about 586 W/m²; at 5.2 au it is about 50.3 W/m². Eclipses, attitude, degradation, thermal state and local horizons change usable energy. NASA solar-irradiance reference

The projected collecting area in a simplified power scenario is A = P/(Sηf). For 100 MW, 30% conversion efficiency and an assumed 90% effective availability at 1 au, A is approximately 272,000 m², or 0.272 km². This is active projected collector area, not total structural footprint. The assumed availability must include the chosen eclipse and operating profile; storage, transmission, conditioning, redundancy, margins and end-of-life degradation are otherwise absent.

Space does not provide free cooling. For an isothermal radiating surface with emissivity ε and an idealized cold sink:

Q = ε σ A (T⁴ − T_sink⁴)

Using σ = 5.670374419…×10⁻⁸ W·m⁻²·K⁻⁴ and ε = 0.9, rejecting 100 MW of waste heat to a negligibly warm sink requires about 242,000 m² at 300 K, 76,500 m² at 400 K, or 15,100 m² at 600 K. A is total emitting surface area, not necessarily one-sided panel footprint. These ideal areas omit sunlight, Earth infrared, view-factor obstruction, nonuniform temperature, coating degradation, pumps and contingency margin. Raising temperature shrinks area but constrains materials and processes. The 100 MW electrical collection example and 100 MW waste-heat example are separate scenarios, not an asserted power balance for one plant. NIST 2022 CODATA constants, NASA radiator testing

An industrial proposal should therefore publish both electrical demand and thermal rejection. “Abundant sunlight” does not settle either system’s mass, cost or reliability.

6. Compare the whole lifecycle, with a changing terrestrial baseline

For each impact category k, calculate an inventory rather than a slogan:

I_k = production + transport + operation + maintenance + end-of-life
      − explicitly justified substitution credits

Divide by qualified lifetime service to obtain impact per functional unit. Use separate entries for climate forcing, ozone, water, land, biodiversity, hazardous releases, debris, reentry risk and resource depletion; many cannot responsibly be collapsed into one unqualified score. Prevent double counting of recycling credits and avoided launches. Show the time dependence of a decarbonizing Earth-side comparator.

NASA’s 2024 assessment of two representative space-based solar-power designs illustrates the discipline. It studied hypothetical 2050 systems, found baseline lifecycle electricity costs substantially above terrestrial alternatives, and identified combinations of improvements needed for competitiveness. Its greenhouse-gas comparison also retained uncertainty about upper-atmosphere launch effects. The report supports further analysis, not a conclusion that orbital power is already the preferred way to decarbonize Earth. NASA Space-Based Solar Power study

The decision should survive conservative ranges for throughput, lifetime, launch burden, replacement rate and terrestrial improvement. An advantage existing only in the most favorable corner remains a research hypothesis.

7. Treat orbit as a shared environment

ESA’s statistics updated 31 July 2026 list approximately 47,070 tracked objects and more than 17,000 tonnes of objects in Earth orbit. Its modeled populations use a separate reference epoch and include many smaller untracked fragments. A tracked-object count and a modeled debris population must not be presented as the same census. ESA Space Environment Statistics

Every new industrial node should therefore carry a collision-avoidance and traffic-coordination concept, fault containment, passivation, repair access, end-of-life responsibility and a funded disposal plan. Reentry removes an orbital object while creating a different atmospheric and ground-risk question. Moving industrial burdens into orbit cannot mean abandoning responsibility for them. ESA’s 2026 report provides an empirical context for this constraint; it does not certify an individual proposed installation. ESA Annual Space Environment Report, 2026

The policy proposals here are transparent authorization, continuing supervision, public environmental accounting, access to challenge evidence, and repair/removal responsibility. Existing legal requirements still apply. The Outer Space Treaty distinguishes non-appropriation, national responsibility, jurisdiction, and due regard/harmful contamination. A project named “System State” does not create sovereignty, licensing power or permission to act. United Nations treaty text, Articles II, VI, VIII and IX

8. Keep ambitious transport research outside the dependency chain

Earth space elevators, momentum-exchange tethers and other major transport concepts may be studied as long-range research paths. Their appearance in the atlas is a scenario, not an operational route. Load paths, manufacturable specific strength, defects, fatigue, environmental exposure, debris strikes, dynamic stability, collision coordination, repair and failure consequences all require evidence.

An Earth elevator is not required to begin useful work on servicing, in-space fabrication, repair or lower-impact launch operations. No blanket prohibition on existing transport should take effect merely because an aspirational substitute is drawn. Any proposed restriction needs demonstrated replacement capacity, service continuity, emergency provisions and legitimate authority. The revised principle is verified substitution before dependency, not dependence on a promised megastructure.

9. What USST contributes to an engineering record

USST can make assumptions and transformations travel with a state. It cannot produce missing observations or operational authority. A proposed installation, transfer or maintenance event should preserve:

• Event type and time scale, numerical time, epoch and precision; emission and reception are different events.
• Object identity; position and velocity; origin, axes, units and dynamical model; coverage and interpolation status.
• Data provider, retrieval date, source solution and raw-data checksum; a checksum establishes byte consistency, not truth.
• Local body/meridian/rotation model where a planetarydian is used; a solardian display preserves its Sun-centered and angular conventions.
• Clock model and uncertainty when proper-time conversion is available; otherwise explicit absence.
• Scenario parameters, technical maturity, environmental accounting, evidence status, responsible reviewer and revision history.

The proposed elapsed-TCB USST label uses an existing time scale and a selected epoch. IAU’s defined TCB–TDB relationship supplies the mathematical basis. Displaying related time labels does not silently convert TDB-compatible spatial quantities or implement a physical timing service. IAU 2006 Resolution B3, NAIF time subsystem

This is where the atlas becomes useful infrastructure: not by claiming to command the system, but by allowing another reader or program to reconstruct what a proposed number, event or comparison means.

10. A deployment sequence with evidence gates

Observe and record. Publish sourced states, time/frame contracts and uncertainty boundaries. Keep measured/fetched inputs, calculations and hypothetical scenarios visibly distinct.

Demonstrate a bounded service. Select a concrete part, material or resource at a named destination. Measure yield, quality, energy, heat, maintenance, waste and availability. Preserve failures.

Compare independently. Audit the full service against terrestrial improvement and demand reduction. Stress-test the result under conservative assumptions and alternative interpretations.

Scale only what survives. Increase throughput after the testable advantage, operating authority, collision/disposal provisions and protection of affected communities are established. Retain stop and revision criteria.

Preserve Earth throughout. No speculative future return should excuse avoidable present harm. Biosphere protection, public benefit and freedom of participation are the purpose; the industrial location is a means to evaluate.

Earth for life. Space for useful work that earns its place. Build outward with evidence, and keep responsibility attached to every step.

---

Prepared as a proposed technical statement for System State Atlas 2.0, 27 September 2026. Numerical examples are declared screening scenarios calculated from the stated equations and constants; they are not facility designs, mission approvals or forecasts. Scientific references support identified facts and mechanisms, not endorsement of the proposal. The numerical assumptions are repeated in the appendix below so that these screening calculations can be independently reproduced.

Numerical appendix / declared screening assumptions

Orbit example:
Earth GM = 398600.435507 × 10⁹ m³/s²
Reference radius = 6378137 m; altitude = 400000 m
Rotation = 7.292115 × 10⁻⁵ rad/s
Energy difference = 32983254.9 J/kg = 9.1620 kWh/kg

Solar collection example:
P = 100000000 W; S = 1361 W/m²; η = 0.30; f = 0.90
A = P/(Sηf) = 272131 m²

Separate heat-rejection example:
Q = 100000000 W; ε = 0.90; ideal sink = 0 K
σ = 5.670374419 × 10⁻⁸ W·m⁻²·K⁻⁴
A(300 K) = 241914 m²
A(400 K) = 76543 m²
A(600 K) = 15120 m²

Mass-accounting example:
q = 10000 kg/year; L = 10 years; c = 0.10
Imported plant + spares + replacements = 20000 kg
Net avoided imports = 70000 kg over assumed service life
Mass break-even = 2.2222 years

Displayed values are rounded. Numerical agreement with these equations would establish arithmetic consistency, not validate the assumed facility, its environmental benefit or its operating life.

Primary source register

Sources checked 27 September 2026. Project proposals, model outputs and measurements retain their different statuses.

1. NASA MOXIE completion recordObserved technology outcome · 122 g oxygen total; 12 g/hour peak; at least 98% purity. A demonstration, not an industrial plant.
2. ESA first metal part printed in spaceObserved technology outcome · First complete part in August 2024; qualification remains separate.
3. ESA examination of the returned metal partObserved technology outcome · November 2025 examination of the returned part.
4. NASA In-Space Manufacturing Portfolio Plan, 2025Institutional technical memorandum · The intended Refabricator recycling demonstration was not completed; preserve the failure.
5. JPL astrodynamic parametersDeclared constants/ephemeris parameters · DE440 Earth GM 398600.435507 km³/s²; exact au and c; these constants do not establish a mission result.
6. Brown et al., 2024: worldwide rocket emissions inventoryPrimary research inventory · 2019 inventory and species/altitude dependence; not a current 2026 total.
7. Maloney et al., 2022: rocket black-carbon atmospheric modelPrimary research scenario · Scenario traffic and stratospheric response; different launch systems are not equivalent.
8. NASA Solar IrradianceReference measured scale · 1361 W/m² reference; variable with solar activity. The inverse-square examples are authored calculations.
9. NIST 2022 CODATA complete constantsSI-derived constant · Stefan–Boltzmann constant 5.670374419… × 10⁻⁸ W m⁻² K⁻⁴.
10. NASA heat-pipe radiator testPrimary technical experiment · Radiative heat-transfer model; the statement scenario areas are not this hardware’s measured performance.
11. NASA 2024 Space-Based Solar Power studyInstitutional lifecycle study · Two hypothetical 2050 systems; higher baseline costs; assumption-sensitive results and upper-atmosphere uncertainty.
12. ESA Space Environment Statistics, 31 July 2026Dated aggregate statistics · About 47,070 tracked objects and more than 17,000 tonnes; modeled small-object populations have a separate February 2026 epoch.
13. ESA Space Environment Report 2026, issue 10Annual institutional assessment · Orbital environment monitoring; not certification of an individual installation.
14. United Nations Outer Space TreatyTreatytext · Articles II, VI, VIII and IX; source text, not a legal opinion or permit.
15. IAU 2006 Resolution B3Defined coordinate-timescale relation · The TCB/TDB definition does not endorse USST.
16. NAIF SPICE time subsystemPrimary technical documentation · Clocks and time scales require declared models.