# Earthwalk: ISS fidelity rubric

Approved requirements · 5 September 2026

**40 station parts × 10 checks = 400 station checks. Six additional gates × 10 = 60 checks. Plus B.01 branding on both astronaut and ISS. Total: 461. See the evidence ledger for current assessments.**

## The target

Build a convincing, one-to-one ISS at metre scale, beautiful in a full-station view and credible when an astronaut approaches a joint, window, rail, solar wing, or radiator. Keep the astronaut appearance you approved and add natural limb motion. Make Earth sharper, its clouds move slowly, and the station actually orbit it.

This is the approved acceptance rubric, dated 5 September 2026. It contains 40 station rubrics with 10 distinct visual checks each: 400 station checks. Six additional ten-check gates cover animation, controls, Earth, orbit, interiors, and scene-wide acceptance: 461 checks in total including one branding criterion assessed on both the suit and ISS. These are approved requirements. Current assessments and unresolved defects are recorded separately in the evidence ledger and review report.

Approved by the user on 5 September 2026. Implementation is underway. The OpenAI logo requirement is added as B.01, without replacing any of the 400 station checks.

## What one-to-one means here

Approved configuration: the permanent station immediately after the 15 June 2023 spacewalk, with six installed iROSA wings. Before modeling, freeze a configuration ledger with a reference timestamp, module connections, transferred hardware, external payloads, visiting vehicles, and articulated poses. Check the ledger against dated photographs; never mix incompatible installation eras. The exact pose and visiting-vehicle manifest are still to be researched, not silently assumed.

Every visible station assembly must match its real shape, size, position, orientation, construction, and material as far as the evidence establishes. Use published dimensions for metre-scale geometry and matched photographs for local features. A convincing generic module cannot pass as the real module.

Forty is the number of review packages, not a claim that the ISS has only forty physical parts. Repeated wings, platforms, adapters, radiators, and payloads receive separate child-instance records. Their lowest result controls the package; they are not averaged together. Antennas, tanks, plumbing, and small equipment belong to their actual host assembly. Visiting vehicles receive child rubrics using the same ten-category evidence method, beyond the base 400, once the manifest is fixed.

The approved Armstrong suit is intentionally retained as a historical avatar; it is not relabeled as a period-correct ISS EMU. View-button transitions between inside and outside remain acceptable. Door animation is optional. All player-accessible interiors must follow the actual module arrangement.

Unknown or obscured details remain marked Unverified. A plausible reconstruction may be used in an interim candidate, but it cannot be described as a verified one-to-one match. If sources conflict, resolve their dates and provenance before changing the model.

## Evidence required for every part

Create a reference board with source URL, agency/creator, image identifier, capture date, usage terms, relevant crop, dimensions, and confidence. Begin with the official reference anchors linked below, then collect part-specific photographs. Those anchors are not yet 400 completed reference comparisons.

Capture forward, aft, port, starboard, zenith, and nadir views, plus two three-quarter views, a critical junction close-up, and an underside/back-side close-up: at least ten rendered views per package. For repeated hardware, repeat the affected views per instance. Add a slow full orbit and close flyby. Capture first at the nearest permitted camera distance, then at roughly 5–15 m and station-wide distances, adjusted to the assembly size.

For comparison, match camera direction, perspective, framing, configuration, appendage pose, and lighting. Use side-by-side crops and silhouette/landmark overlays. Do not distort the render to force an overlay fit or use screenshots with unmatched exposure as proof of material accuracy. At least three distinct source angles per assembly are the collection target; if coverage is unavailable, name the unverified surface.

Use shaded beauty, neutral-light, wireframe, normal, and material-isolation views to diagnose faults. These diagnostic passes support the final native-resolution beauty and motion captures; they cannot replace them. Keep the Sun, camera exposure, and color handling recorded for reproducibility.

Every check gets an evidence row: check ID, child instance, build ID, source image IDs, camera/lighting preset, render or clip, measured result, score, status, defect, and retest result. No screenshots from an older candidate can prove a changed candidate passes.

## Scoring and rejection rules

Score each check from 0–10, with Unverified kept separate from zero. 0 = missing; 1–4 = substantially wrong or broken; 5 = functional prototype with obvious approximation; 6–7 = recognizable but visibly inaccurate; 8 = close with an identifiable mismatch; 9 = reference-supported match with only minor, documented uncertainty and no visible defect in the tested views; 10 = no reproducible discrepancy within the documented source precision and viewing coverage. Ten is not a claim of absolute perfection.

Acceptance: every required check must score at least 9 and have its evidence attached. Each package reports its minimum score, not an average. Wrong module placement, missing required hardware, visible clipping, exposed mesh intersections, floating supports, broken animation, or unresolved configuration mismatches are hard failures regardless of score.

Dimensional tolerance: for a reliably dimensioned major body or assembly, error must be no more than the larger of 0.5% and the published measurement uncertainty. For matched image landmarks, target a median error at most 1% and a maximum at most 2% of the assembly image bounding-box diagonal. These are project QA thresholds, not NASA tolerances, and cannot excuse a visibly wrong feature. If camera calibration or reference precision is inadequate, mark the measurement Unverified.

Configuration identity, port connections, assembly counts, and mirrored orientation require exact agreement with the frozen ledger. Exposed cracks, unintended overlaps, flicker, missing faces, and clipping in reachable views have zero allowed reproducible occurrences. Intentional mechanical nesting and hidden construction overlaps are acceptable only when they produce the referenced physical appearance.

Every new asset must pass the same tests. Inspect mesh quality, scale, normals, UVs, texture resolution, material response, license, and configuration before accepting it. Real-world provenance is useful evidence, not a quality exemption.

A check may be marked Not applicable only with a written reason that the feature truly does not exist in that instance. Missing references, difficult modeling, or performance cost do not justify N/A. Replacement checks must preserve the ten-check coverage. Do not silently lower thresholds to make a candidate pass.

## How iteration will work after review

1. Freeze the current suit and working controls as a comparison baseline. Build the dated station inventory and reference boards. Resolve module layout, dimensions, attachment axes, visiting vehicles, and appendage poses before detailed art work.

2. Reconstruct the station at the correct scale using simple diagnostic geometry. Compare all major silhouettes and connection points. Reject incorrect proportions or layout now; surface detail cannot repair them.

3. Work through the 40 packages: structure and joints, secondary equipment, materials, then close-up details. After each pass, capture the prescribed views, enter defects, correct them, and repeat the affected comparisons. Recheck neighboring parts whenever an interface changes.

4. Rig and animate the approved suit, implement independent camera orbit/body control, improve Earth, and add orbital motion. Evaluate their separate gates and recheck station contacts, lighting, camera behavior, and performance.

5. Run isolated Playwright self-play with repeatable inputs, native screenshots, motion clips, console inspection, and named collision routes. Review the visible results yourself in the captured frames; automated assertions do not establish visual fidelity.

6. Perform a fresh whole-scene review against the full ledger, including back sides and difficult angles. Keep dated before/after captures and rejected candidates. Repeat while required defects remain; neither a green test suite nor an arbitrary iteration count is a stopping rule.

7. Finish only when the exact candidate passes the complete ledger and the final evidence package is reviewable. If evidence, asset availability, or hardware limits prevent a requirement from passing, report that specific gap and keep the fidelity claim bounded; do not rename incomplete work as complete.

## The 40 station rubrics

### S01 — Unity · Node 1

Shell, port collars, exposed fittings, and the visible vestibules; connected modules have their own rubrics.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/). Part-specific comparison evidence is pending.

1. **S01.01** — Match the measured cylinder length, diameter, end profiles, and port-center spacing in orthographic overlays.
2. **S01.02** — Verify every occupied and unused port against the frozen configuration; a plausible-looking but wrong connection fails.
3. **S01.03** — Match axial and radial collar depth, flange steps, hatch recesses, and insulation transitions in oblique views.
4. **S01.04** — Reconstruct the visible shielding-panel layout; reject uniformly repeated panels where the reference is asymmetric.
5. **S01.05** — Place exterior rails and their standoffs from photographs; check clearance between rails and the pressure-shell covering.
6. **S01.06** — Resolve exposed cable exits, connectors, and brackets as attached hardware, without wires vanishing into arbitrary surfaces.
7. **S01.07** — Match white shielding, blanket seams, and exposed metal separately under calibrated sunlight and Earth fill.
8. **S01.08** — Compare forward, aft, port, starboard, zenith, and nadir views; adjacent modules must neither hide errors nor intersect Unity.
9. **S01.09** — Inspect port interiors from the accessible corridor: wall thickness, hatch-frame depth, and structural seams remain continuous.
10. **S01.10** — Sweep a close camera around the module; reject faceted curves, flipped triangles, texture swimming, and flashing seams.

### S02 — Harmony · Node 2

Node body and attachment interfaces; docking adapters are reviewed in part 22.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/). Part-specific comparison evidence is pending.

1. **S02.01** — Match Harmony's length-to-diameter ratio and end taper to dimensional and photographic references.
2. **S02.02** — Verify its actual connection to Destiny and the lateral positions of Columbus and Kibo; no mirrored layout.
3. **S02.03** — Check the forward and zenith docking-interface positions and orientation against the selected configuration.
4. **S02.04** — Compare each visible shielding strip and collar interruption rather than duplicating Unity's surface pattern.
5. **S02.05** — Match handrail lengths, gaps, bracket feet, and access paths around protruding equipment.
6. **S02.06** — Place grapple and utility fittings at referenced mounting points, with their bases seated on the module.
7. **S02.07** — Inspect docking-adapter junctions from underneath for floating flanges, shell penetration, and incorrect gasket depth.
8. **S02.08** — Match blanket texture scale and metal roughness without embossing the entire body with oversized fabric weave.
9. **S02.09** — Compare the node's silhouette with both laboratories attached from front, top, bottom, and rear.
10. **S02.10** — Inspect a moving close-up through the node and around its exterior; panel joins and collar shading stay stable.

### S03 — Tranquility · Node 3

Node shell, ports, and visible interior junctions; its attached modules are separately scored.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/); [R4: ESA · European contributions](https://www.esa.int/Science_Exploration/Human_and_Robotic_Exploration/Node-3_Cupola/ISS_and_Europe_s_Major_Contributions). Part-specific comparison evidence is pending.

1. **S03.01** — Match the real node proportions and its orientation relative to Unity, with dimensional evidence.
2. **S03.02** — Map Cupola, Leonardo, BEAM, and Bishop to their correct dated ports; no arbitrary radial arrangement.
3. **S03.03** — Check occupied and capped port collar shapes from below and both ends of the node.
4. **S03.04** — Match shielding segmentation around the closely packed attachments; panel seams must terminate at real boundaries.
5. **S03.05** — Reproduce observed rails, brackets, and cable runs with a visible physical attachment at each end.
6. **S03.06** — Check clearance between adjacent attached modules and the node's exterior hardware from the narrowest viewing gaps.
7. **S03.07** — Match blanket folds, hard shielding, and rim metal as different surfaces under the same light.
8. **S03.08** — Inspect the Cupola junction from outside and inside; the viewing direction and passage alignment must agree.
9. **S03.09** — Compare the node and its attachments in a matched nadir view, preserving the reference's crowded but purposeful silhouette.
10. **S03.10** — Orbit the camera through the entire cluster; reject disappearing walls, overlapping skins, and unsupported equipment.

### S04 — Destiny laboratory

Laboratory shell, observation-window hardware, external interfaces, and visible laboratory interior.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/); [R14: NASA · Destiny robotics workstation](https://www.nasa.gov/image-article/robotic-workstation-destiny-lab/). Part-specific comparison evidence is pending.

1. **S04.01** — Match the laboratory's long cylindrical profile, end geometry, and measured scale relative to an astronaut.
2. **S04.02** — Verify its axial connections to Unity and Harmony and its relationship to the central truss support.
3. **S04.03** — Match longitudinal shielding rows, circumferential breaks, and end-cap panel shapes in reference overlays.
4. **S04.04** — Place the observation-window opening and protective hardware on the correct side and at the correct longitudinal position.
5. **S04.05** — Inspect the window recess, rim thickness, glazing, and frame contact from inside and outside.
6. **S04.06** — Match external rails, fixtures, and support interfaces; reject evenly spaced decorative hardware without references.
7. **S04.07** — Check that the S0 support attachments meet the correct shell locations without visually penetrating the laboratory.
8. **S04.08** — Match laboratory rack spacing and passage dimensions in the explorable portion using interior photographs.
9. **S04.09** — Compare white shielding, glass, exposed metal, and interior textiles without flattening all materials into one finish.
10. **S04.10** — Traverse the corridor and orbit the exterior at close range; window edges, rack faces, and shell seams remain stable.

### S05 — Columbus laboratory

Laboratory body, mounting hardware, and dated external payload interfaces.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/); [R4: ESA · European contributions](https://www.esa.int/Science_Exploration/Human_and_Robotic_Exploration/Node-3_Cupola/ISS_and_Europe_s_Major_Contributions). Part-specific comparison evidence is pending.

1. **S05.01** — Match Columbus's compact proportions, end caps, and docking neck against module photographs and dimensions.
2. **S05.02** — Verify its side of Harmony and its axial orientation; a mirrored laboratory fails even if the silhouette looks attractive.
3. **S05.03** — Reproduce the module-specific exterior panel divisions and their seams at the end caps.
4. **S05.04** — Match the visible external payload mounting structures, including thickness and support feet.
5. **S05.05** — Inventory payloads against the chosen date; do not copy a launch-era installation into the modern configuration unchecked.
6. **S05.06** — Inspect handrails, labels, utility fittings, and their positions relative to the shielding boundaries.
7. **S05.07** — Compare the attachment neck and underside from oblique views for collars passing through the parent module.
8. **S05.08** — Match insulation and metal reflectance with the reference exposure normalized; avoid a uniformly chrome or plastic body.
9. **S05.09** — Check the visible interior rack arrangement and hatch direction against Columbus interior imagery.
10. **S05.10** — Sweep from a station-wide view to a one-metre approach; silhouette, fine detail, and texture sharpness remain coherent.

### S06 — Kibo pressurized module

Main Japanese laboratory, end hardware, module airlock exterior, and visible interior.

Reference anchors: [R3: JAXA · Kibo](https://humans-in-space.jaxa.jp/en/kibo/). Part-specific comparison evidence is pending.

1. **S06.01** — Match the main laboratory's dimensions and the relative sizes of its cylindrical body and end structures.
2. **S06.02** — Verify the connection to Harmony and the placement of the logistics module and exposed facility around it.
3. **S06.03** — Match shielding strips, end-cap segmentation, and characteristic interruptions to the cylindrical silhouette.
4. **S06.04** — Reconstruct the experiment-airlock opening and adjacent structure at the photographed position and scale.
5. **S06.05** — Check the robotic-arm base interface and nearby fittings against JAXA imagery, without moving them for convenience.
6. **S06.06** — Match rail runs and external utility routing around the end of the laboratory.
7. **S06.07** — Inspect the exposed-facility junction for real brackets, correct spacing, and no intersecting shell surfaces.
8. **S06.08** — Compare white panels, blanket-covered fittings, window glass, and bare metal under one lighting setup.
9. **S06.09** — Match interior passage width, rack faces, and window/airlock relationships in the accessible area.
10. **S06.10** — Compare front, rear, underside, and elevated approach footage; no major feature may disappear at a detail transition.

### S07 — Kibo logistics module · ELM-PS

Pressurized logistics section and its attachment; obsolete exposed logistics hardware must not be added from old diagrams.

Reference anchors: [R3: JAXA · Kibo](https://humans-in-space.jaxa.jp/en/kibo/). Part-specific comparison evidence is pending.

1. **S07.01** — Match the short cylinder's proportions, end contour, and diameter relative to the main Kibo laboratory.
2. **S07.02** — Verify the attachment location, axis, and rotational orientation against the frozen configuration.
3. **S07.03** — Compare the coupling neck and ring stack from multiple sides for correct length and flange depth.
4. **S07.04** — Match exterior panel and blanket boundaries without recycling the main laboratory's texture arrangement.
5. **S07.05** — Place the photographed grapple fitting and external access hardware with correctly scaled brackets.
6. **S07.06** — Check handrail spacing and projection from the skin in close-up side views.
7. **S07.07** — Inspect the lower junction and nearby structures for contact errors hidden in a frontal photograph.
8. **S07.08** — Match seams and blanket wrinkles at a realistic scale; reject coarse noise used to simulate detail.
9. **S07.09** — Verify visible identification markings against source orientation and prohibit mirrored lettering.
10. **S07.10** — Perform a full close orbit of the module; curved highlights, end-cap triangulation, and joints must remain clean.

### S08 — Kibo exposed facility

Facility platform, attached experiment units and communications hardware present in the selected configuration.

Reference anchors: [R3: JAXA · Kibo](https://humans-in-space.jaxa.jp/en/kibo/). Part-specific comparison evidence is pending.

1. **S08.01** — Match the platform outline, thickness, and supporting geometry to top, side, and underside references.
2. **S08.02** — Verify its location and alignment at the end of the pressurized module.
3. **S08.03** — Map each payload site to the dated inventory; empty and occupied positions must match the reference.
4. **S08.04** — Reconstruct the visible shapes of each installed experiment rather than filling sites with generic white boxes.
5. **S08.05** — Match payload attachment mechanisms, support brackets, and interfaces at close range.
6. **S08.06** — Check exposed cable and utility routing across the platform for supported paths and credible terminations.
7. **S08.07** — Inspect underside equipment and structure; the platform must not become a featureless slab from below.
8. **S08.08** — Match blanket, structural metal, experiment covers, and dark apertures as distinct materials.
9. **S08.09** — Compare payload heights and gaps in a low grazing view; reject intersecting instruments or floating mounting feet.
10. **S08.10** — Fly around all platform edges and beneath it; thin parts and instrument silhouettes must remain stable in motion.

### S09 — Kibo robotic arm · JEMRMS

Main arm and any smaller arm/tool present in the frozen pose, including their mounts.

Reference anchors: [R3: JAXA · Kibo](https://humans-in-space.jaxa.jp/en/kibo/). Part-specific comparison evidence is pending.

1. **S09.01** — Match arm-segment lengths and joint housing sizes to JAXA dimensional and photographic references.
2. **S09.02** — Verify the base position and axis on Kibo, including the complete mounting connection.
3. **S09.03** — Match the documented reference pose; do not invent a convenient bend that intersects station equipment.
4. **S09.04** — Inspect each joint's axis, overlapping mechanical covers, and gap so the arm reads as a connected mechanism.
5. **S09.05** — Reconstruct the end effector, camera housings, and visible tool fittings instead of a rounded stump.
6. **S09.06** — Match blanket seams and exposed joint metal with plausible local texture scale.
7. **S09.07** — Route visible harnesses around joints without stretching across open gaps or entering solid housings incorrectly.
8. **S09.08** — Check the arm from front, rear, underside, and end-on for collapsed geometry and broken attachment continuity.
9. **S09.09** — Compare the arm's size and clearance above the exposed facility in a matched wide reference view.
10. **S09.10** — Inspect close moving footage through the joint chain; fine fittings must not flicker or merge into nearby payloads.

### S10 — Cupola

Exterior dome, glazing, shutters, interior window frames, and visible observation workstation.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/); [R4: ESA · European contributions](https://www.esa.int/Science_Exploration/Human_and_Robotic_Exploration/Node-3_Cupola/ISS_and_Europe_s_Major_Contributions). Part-specific comparison evidence is pending.

1. **S10.01** — Match the dome proportions and the central and surrounding window arrangement to measured reference views.
2. **S10.02** — Verify its Earth-facing mounting direction and the exact junction to Tranquility.
3. **S10.03** — Match the shape, thickness, bevels, and alignment of every window frame, inside and outside.
4. **S10.04** — Model each shutter with visible hinges and the chosen open/closed pose; no unsupported floating covers.
5. **S10.05** — Check glazing thickness, reflections, transmission, and tint against photographs without obscuring Earth's view.
6. **S10.06** — Inspect interior-to-exterior continuity at each pane; no double frames, wall leaks, or mismatched window openings.
7. **S10.07** — Reproduce the visible interior equipment, handholds, and cable placement with a clear observation space.
8. **S10.08** — Compare real wear, insulation, and frame materials in controlled daylight rather than adding arbitrary grime.
9. **S10.09** — Match the Earth horizon and station obstruction through each window from a physically plausible viewing position.
10. **S10.10** — Move the camera across window edges and outside the dome; reject glass sorting errors, clipping, and unstable reflections.

### S11 — Quest airlock

Equipment lock, crew lock, external tanks, exit frame, and visible interior. Door animation is optional.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/). Part-specific comparison evidence is pending.

1. **S11.01** — Match the two connected chamber proportions, diameter change, and end contours against references.
2. **S11.02** — Verify the airlock's mounting point and orientation relative to Unity.
3. **S11.03** — Match the exterior gas-tank count, shapes, locations, supports, and straps to the selected configuration.
4. **S11.04** — Reconstruct the EVA exit opening and rim with real depth and correctly positioned neighboring handrails.
5. **S11.05** — Match external shielding, insulation seams, hatch markings, and access fittings to close reference photographs.
6. **S11.06** — Inspect the chamber junction and tank brackets from below for floating supports and exposed intersections.
7. **S11.07** — Reproduce the visible crew-lock interior volume, handholds, and suit-clearance envelope at actual scale.
8. **S11.08** — Match painted shielding, metal tank hardware, seals, and textile surfaces without identical roughness.
9. **S11.09** — Compare the full EVA approach and exit composition from both sides of the frame.
10. **S11.10** — Inspect the astronaut passing through a clear exit or using the view transition; no suit, tether, or camera penetration.

### S12 — Leonardo permanent multipurpose module

Cargo module shell, its present attachment, and any visible storage interior.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/). Part-specific comparison evidence is pending.

1. **S12.01** — Match the module's length, diameter, and end-cap profile to photographs and dimensions.
2. **S12.02** — Verify its June 2023 attachment location; launch and earlier berthing photographs are not location evidence.
3. **S12.03** — Match collar depth and the offset between the main body and attached node.
4. **S12.04** — Reproduce shielding bands and module-specific panel seams, including the end-cap transitions.
5. **S12.05** — Check exterior rails, grapple fittings, and bracket feet against source positions.
6. **S12.06** — Match visible labels and blanket closures without repeating generic markings around the cylinder.
7. **S12.07** — Inspect the crowded junction with Tranquility and neighboring modules from the underside.
8. **S12.08** — Compare shielding, insulation, and exposed rim metal with nearby modules under identical lighting.
9. **S12.09** — If visible inside, match cargo bag dimensions, restraint locations, and usable passage clearance to reference imagery.
10. **S12.10** — Sweep all accessible exterior sides and the visible interior; no floating bags, shell clipping, or unstable panel edges.

### S13 — BEAM expandable module

Expanded envelope, rigid ends, mounting collar, and visible external hardware.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/). Part-specific comparison evidence is pending.

1. **S13.01** — Match the expanded envelope's measured length, maximum width, and end-to-middle profile.
2. **S13.02** — Verify its actual mounting port and orientation on Tranquility.
3. **S13.03** — Match the fabric envelope's broad contour and seam placement without inflating it into a perfectly smooth balloon.
4. **S13.04** — Reproduce the transition from flexible envelope to rigid end structures with correct thickness and contact.
5. **S13.05** — Match the collar stack and attachment depth from side and underside photographs.
6. **S13.06** — Place observed straps, seams, access fittings, and markings on their referenced parts of the envelope.
7. **S13.07** — Compare soft blanket roughness with adjacent hard shielding under the same sunlight.
8. **S13.08** — Check silhouette shading for pinching triangles, lumpy tessellation, and exaggerated normal-map wrinkles.
9. **S13.09** — Inspect clearance to nearby modules, rails, and the Cupola cluster from the narrowest angles.
10. **S13.10** — Orbit close to both ends and along the envelope; no seam crawling, texture stretching, or detached end caps.

### S14 — Bishop airlock

Airlock shell, berth interface, external mounting sites, and payloads present in the dated scene.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/). Part-specific comparison evidence is pending.

1. **S14.01** — Match the distinctive shell outline and dimensions rather than substituting a generic cylinder.
2. **S14.02** — Verify its berth and orientation on Tranquility for the chosen reference date.
3. **S14.03** — Match the opening rim, attachment collar, and rear geometry from front and side photographs.
4. **S14.04** — Reconstruct exterior shielding facets and seams with clean, intentional panel intersections.
5. **S14.05** — Locate grapple fittings and their mounting plates at the correct scale and orientation.
6. **S14.06** — Inventory visible payload brackets and installed hardware against dated photographs.
7. **S14.07** — Inspect the underside and mounting junction for unsupported brackets and collars penetrating the node.
8. **S14.08** — Match blanket-covered areas, hard panels, and exposed metal with appropriate separate materials.
9. **S14.09** — Check its silhouette against BEAM, Cupola, and Leonardo in the same wide reference view.
10. **S14.10** — Fly around the airlock at close range; rims, fine mounts, and panel joins stay stable without hiding defects in shadow.

### S15 — Zarya

Complete module, its solar-array configuration, external fittings, and relevant docking interfaces.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/). Part-specific comparison evidence is pending.

1. **S15.01** — Match the stepped body, tapered sections, end structures, and measured proportions to dated photographs.
2. **S15.02** — Verify its orientation and connections to the U.S. and Russian station segments.
3. **S15.03** — Match the actual solar-array deployment state in June 2023; older photographs cannot silently determine the pose.
4. **S15.04** — Reconstruct panel blankets and thermal-cover boundaries around each change in body diameter.
5. **S15.05** — Locate external tanks, conduits, antennas, and brackets from an itemized host-module inventory.
6. **S15.06** — Check docking-collar and adapter geometry from end-on and oblique views.
7. **S15.07** — Inspect array roots, hinges, and any folded structure for connected, nonintersecting geometry.
8. **S15.08** — Match insulation coloration and exposed hardware finish without painting the whole module one uniform color.
9. **S15.09** — Compare top, underside, and both side silhouettes, including asymmetric external equipment.
10. **S15.10** — Fly along the entire module and around its ends; cable routes, seams, and thin appendages remain clean in motion.

### S16 — Zvezda service module

Service-module body, arrays, antennas, windows, docking end, and exterior equipment.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/). Part-specific comparison evidence is pending.

1. **S16.01** — Match each stepped body section, tapered transition, and docking-end proportion to measured references.
2. **S16.02** — Verify its axis, connection to Zarya, and spatial relationship to attached Russian modules.
3. **S16.03** — Match both solar wings, their cell patterns, root geometry, and documented deployment orientation.
4. **S16.04** — Place visible windows and their frame/recess geometry accurately along the body.
5. **S16.05** — Inventory antenna shapes, booms, dishes, and mounting points against dated photographs.
6. **S16.06** — Match thermal blankets, access-panel boundaries, rails, and cable routes around the asymmetric exterior.
7. **S16.07** — Inspect the aft docking region and external thruster hardware in close reference views without inventing nozzle detail.
8. **S16.08** — Compare blanket reflectance, array coloration, glazing, and exposed metal under consistent lighting.
9. **S16.09** — Check all module and array clearances from top, underside, front, and rear.
10. **S16.10** — Orbit the full service module; no faceted tapers, disconnected booms, texture repetition, or flashing array edges.

### S17 — Poisk

Mini-research module, docking end, access hardware, and its station attachment.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/). Part-specific comparison evidence is pending.

1. **S17.01** — Match the compact body's contour, dimensional proportions, and end profile against Poisk-specific references.
2. **S17.02** — Verify the correct attachment point and outward direction; do not substitute Pirs geometry or location.
3. **S17.03** — Match the docking-end rim, recesses, and attachment depth from axial and side views.
4. **S17.04** — Reconstruct the exterior hatch shape and its position relative to the body seams.
5. **S17.05** — Place handrails, foot restraints, and brackets at photographed locations with correct standoff distances.
6. **S17.06** — Match blanket seams, straps, labels, and access-cover edges without generic repeated details.
7. **S17.07** — Check attached antenna and utility hardware against the dated inventory for this module.
8. **S17.08** — Compare the module's material response and weathering with adjacent Russian-segment surfaces.
9. **S17.09** — Inspect the root connection and every exterior fitting from underneath for floating or intersecting geometry.
10. **S17.10** — Fly around the entire contour at astronaut distance; hatch rims, rounded sections, and small brackets remain stable.

### S18 — Rassvet

Mini-research module and its dated external equipment; transferred hardware must be removed from obsolete positions.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/). Part-specific comparison evidence is pending.

1. **S18.01** — Match the module's body proportions, narrowed sections, and docking-end geometry to reference dimensions.
2. **S18.02** — Verify the mounting point and orientation relative to Zarya and the rest of the Russian segment.
3. **S18.03** — Map external equipment to June 2023 after relevant transfers; reject copying an earlier cargo configuration.
4. **S18.04** — Match blanket panel shapes and seam locations around the distinctive body transitions.
5. **S18.05** — Reconstruct the visible docking rim, mechanisms, and surrounding hardware at credible scale.
6. **S18.06** — Place handrails and access fixtures with their exact observed spacing and standoff geometry.
7. **S18.07** — Route visible cables and hoses to real fittings rather than allowing them to disappear into blank surfaces.
8. **S18.08** — Compare insulation, metal, and dark recesses with exposure-matched close-up photographs.
9. **S18.09** — Inspect the crowded mounting junction from several oblique views for unintended overlaps.
10. **S18.10** — Perform an end-to-end close flyby and full orbit; small fittings, blanket detail, and collar seams stay visually coherent.

### S19 — Nauka multipurpose laboratory

Main body, arrays, transferred experiment airlock and radiator, exterior hardware; ERA is part 21.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/); [R5: ESA · European Robotic Arm](https://www.esa.int/Science_Exploration/Human_and_Robotic_Exploration/International_Space_Station/European_Robotic_Arm). Part-specific comparison evidence is pending.

1. **S19.01** — Match the long stepped body, tapered transitions, and end structures to measured Nauka references.
2. **S19.02** — Verify the station connection and the position of Prichal relative to the main laboratory.
3. **S19.03** — Match solar-wing sizes, cells, hinges, and the deployment pose selected for the dated scene.
4. **S19.04** — Verify the transferred radiator and experiment-airlock locations and deployment state for June 2023.
5. **S19.05** — Reconstruct the ERA base points and their supporting fittings without duplicating the robot itself.
6. **S19.06** — Match exterior blankets, rails, hatch outlines, windows, and identifiable equipment placement.
7. **S19.07** — Inspect the underside, radiator mounting, and airlock junction for missing supports or exposed mesh penetration.
8. **S19.08** — Match the contrast among insulation, photovoltaic surfaces, radiator faces, and bare mechanisms.
9. **S19.09** — Compare the full module silhouette with its appendages from front, rear, nadir, and zenith.
10. **S19.10** — Fly through the reachable gaps around its appendages; geometry, materials, and contact points remain stable in motion.

### S20 — Prichal docking node

Node body, all docking-port interfaces, caps, blankets, and Nauka connection.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/). Part-specific comparison evidence is pending.

1. **S20.01** — Match the node's rounded body dimensions and its relationship to the diameter of each port.
2. **S20.02** — Verify the connection to Nauka and the orientation of every remaining docking port.
3. **S20.03** — Match each port's flange stack, rim shape, recess, and projected length from the node.
4. **S20.04** — Check occupied, capped, and available ports against the frozen scene manifest.
5. **S20.05** — Reproduce thermal blanket segments around the closely spaced port openings without intersecting the rings.
6. **S20.06** — Place photographed rails, external fittings, and cable interfaces in their correct positions.
7. **S20.07** — Inspect the Nauka junction from all reachable sides for alignment and proper structural contact.
8. **S20.08** — Match blanket and docking-ring materials with correct highlight width and shadowed detail.
9. **S20.09** — Compare six directional silhouettes; port symmetry must not erase real differences between individual interfaces.
10. **S20.10** — Orbit closely between the ports; reject missing back faces, intersecting collars, coarse curvature, and unstable seams.

### S21 — European Robotic Arm · ERA

Robot, end effectors, visible harnesses, and contact with its selected Nauka base points.

Reference anchors: [R5: ESA · European Robotic Arm](https://www.esa.int/Science_Exploration/Human_and_Robotic_Exploration/International_Space_Station/European_Robotic_Arm). Part-specific comparison evidence is pending.

1. **S21.01** — Match segment lengths, joint diameters, and the overall extended envelope to ESA specifications.
2. **S21.02** — Verify which end is attached and identify its exact Nauka base point in the chosen reference pose.
3. **S21.03** — Match the shoulder, elbow, and wrist angles in multiple views; perspective alone cannot determine a valid pose.
4. **S21.04** — Reconstruct both end effectors, cameras, and visible local mechanisms instead of using identical featureless caps.
5. **S21.05** — Inspect each joint connection for clean bearing gaps, correctly nested covers, and attached structural members.
6. **S21.06** — Match insulation wraps, seams, exposed joint metal, and reference markings without stretching textures around bends.
7. **S21.07** — Route visible harnesses through supported paths and inspect their clearance at each joint.
8. **S21.08** — Compare the arm against the Nauka silhouette, including clearance from arrays, radiator, and airlock.
9. **S21.09** — Inspect both ends and all joint undersides for disconnected meshes, pinched curves, and hidden intersections.
10. **S21.10** — Move the camera along the entire arm; small fittings and mechanical gaps must remain stable at every approach angle.

### S22 — Pressurized mating adapters and docking adapters

PMA-1, PMA-2, PMA-3, IDA-2 and IDA-3, each with its own instance evidence and parent-port record.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/). Part-specific comparison evidence is pending.

1. **S22.01** — Verify every adapter's identity, host port, direction, and relative rotation in the dated station manifest.
2. **S22.02** — Match each PMA's offset, taper, length, and end-ring proportions; do not replace it with a straight tube.
3. **S22.03** — Match each IDA's ring dimensions, rim profile, and attachment depth independently.
4. **S22.04** — Inspect mating planes for concentric contact, correct offsets, and no visible flange interpenetration.
5. **S22.05** — Reconstruct visible docking petals, guides, covers, and recesses at the level supported by close photographs.
6. **S22.06** — Match blanket segmentation, closure seams, and exposed structural edges on the individual adapter.
7. **S22.07** — Locate rails, cables, and external fittings without obstructing the docking opening.
8. **S22.08** — Compare black/white insulation and metal finishes under the same light as their parent modules.
9. **S22.09** — Inspect every adapter from the docking axis, side, underside, and its narrow rear junction.
10. **S22.10** — Fly past each rim and through any accessible passage; reject floating seals, missing interior walls, and flashing coplanar faces.

### S23 — Z1 truss and mounted equipment

Z1 frame, control-moment-gyro housings, communications hardware, and fittings assigned to this host.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/); [R2: NASA · Integrated truss structure](https://www.nasa.gov/international-space-station/integrated-truss-structure/). Part-specific comparison evidence is pending.

1. **S23.01** — Match the frame's measured envelope and orientation above its actual node attachment.
2. **S23.02** — Reconstruct the observed beam cross-sections and diagonal pattern, including asymmetric frame bays.
3. **S23.03** — Locate each gyro housing and supporting mount from the selected configuration references.
4. **S23.04** — Inventory antenna and communications assemblies hosted here, recording dish, boom, and mount orientation separately.
5. **S23.05** — Match attachment feet and support paths between Z1 and the station without beams ending in empty space.
6. **S23.06** — Reproduce visible equipment boxes and covers by silhouette and mounting depth rather than random box scatter.
7. **S23.07** — Route observed cables and utility bundles through specific frame locations with supports.
8. **S23.08** — Match exposed structure, blanket-covered equipment, and antenna surfaces as different materials.
9. **S23.09** — Inspect all six directions and the interior of open bays for missing structure and unintended intersections.
10. **S23.10** — Fly beneath and through camera-accessible gaps; diagonal edges, cables, and small mounts must remain stable.

### S24 — S0 central truss

Central frame, laboratory support struts, rails, fixed utility hardware; mobile carriage is part 37.

Reference anchors: [R2: NASA · Integrated truss structure](https://www.nasa.gov/international-space-station/integrated-truss-structure/). Part-specific comparison evidence is pending.

1. **S24.01** — Match the central truss dimensions, cross-section, and position relative to Destiny.
2. **S24.02** — Reconstruct the actual bay lengths and diagonal connections rather than repeating a generic lattice cell.
3. **S24.03** — Match laboratory support strut count, attachment points, and load-path geometry to reference views.
4. **S24.04** — Verify alignment and spacing of the mobile-transporter rail surfaces through the central section.
5. **S24.05** — Inventory fixed equipment boxes, covers, and utility interfaces on the correct faces.
6. **S24.06** — Match beam end plates, node connections, and visible fastener scale at astronaut approach distance.
7. **S24.07** — Route reference cable bundles and fluid lines without crossing open travel paths incorrectly.
8. **S24.08** — Match structural metal, white covers, and insulated equipment under common sun and Earth lighting.
9. **S24.09** — Inspect underside attachments and both lateral truss connections for gaps, overlapping beams, and unsupported rails.
10. **S24.10** — Traverse above, below, and alongside S0; thin diagonals and rail edges remain stable without obvious detail popping.

### S25 — P1 truss and port radiator bank

Port inboard structure, its thermal radiator assembly, fixed equipment, and communications fittings.

Reference anchors: [R2: NASA · Integrated truss structure](https://www.nasa.gov/international-space-station/integrated-truss-structure/); [R6: ESA · ISS radiators, Luca Parmitano photograph](https://www.esa.int/ESA_Multimedia/Images/2020/01/International_Space_Station_radiators2). Part-specific comparison evidence is pending.

1. **S25.01** — Match P1's length, cross-section, and connection orientation relative to S0 and P3.
2. **S25.02** — Reconstruct the correct bay pattern, beam profiles, and underside structure in matched views.
3. **S25.03** — Match each radiator panel's outline, segmentation, edge frame, and visible thickness independently.
4. **S25.04** — Verify radiator root hinges and the selected deployment angles against dated references.
5. **S25.05** — Inspect radiator supports and their connection to the truss; sheets cannot hover above the frame.
6. **S25.06** — Match thermal plumbing, cable routes, and equipment mounting arrangements along the port structure.
7. **S25.07** — Inventory antenna and other protruding fittings on this host and compare their local silhouettes.
8. **S25.08** — Match the radiator face/back contrast and frame material without making every surface uniformly white.
9. **S25.09** — Check the back of every radiator and the bank's clearance from adjacent equipment at grazing angles.
10. **S25.10** — Fly parallel to each radiator edge and beneath P1; no paper-thin silhouettes, flashing seams, or detached pipes.

### S26 — S1 truss and starboard radiator bank

Starboard inboard structure, thermal radiators, fixed equipment, and communications fittings.

Reference anchors: [R2: NASA · Integrated truss structure](https://www.nasa.gov/international-space-station/integrated-truss-structure/); [R6: ESA · ISS radiators, Luca Parmitano photograph](https://www.esa.int/ESA_Multimedia/Images/2020/01/International_Space_Station_radiators2). Part-specific comparison evidence is pending.

1. **S26.01** — Match S1 dimensions and its actual relation to S0 and S3 in the station layout.
2. **S26.02** — Reconstruct the starboard-specific bay structure; do not assume all port-side equipment is mirrored.
3. **S26.03** — Match every radiator's panel divisions, edge shape, thickness, and back structure to references.
4. **S26.04** — Verify hinge locations and radiator deployment angles for the frozen scene.
5. **S26.05** — Inspect the bank's supporting structure and each connection to the truss from below.
6. **S26.06** — Map visible pumps, boxes, plumbing, and cables to their correct starboard mounting positions.
7. **S26.07** — Check antenna, light, and protruding utility fittings against the host-specific inventory.
8. **S26.08** — Match radiator face, reverse surface, frame metal, and blanket material under consistent illumination.
9. **S26.09** — Compare the bank's full silhouette and clearance to nearby payloads from front, rear, top, and underside.
10. **S26.10** — Sweep along every radiator and through open visual gaps; reject intersecting sheets, floating mounts, and shimmering edges.

### S27 — P3/P4 truss and array joints

Port inner photovoltaic structure, rotary joint, array roots, local thermal hardware; blankets are part 33.

Reference anchors: [R2: NASA · Integrated truss structure](https://www.nasa.gov/international-space-station/integrated-truss-structure/). Part-specific comparison evidence is pending.

1. **S27.01** — Match P3/P4's structural envelope and its measured placement between P1 and P5.
2. **S27.02** — Reconstruct the correct transition between the truss sections and the photovoltaic structure.
3. **S27.03** — Match the solar alpha rotary joint's diameter, ring depth, housing detail, and rotation axis.
4. **S27.04** — Verify array-root and beta-joint locations against the identified port-side power channels.
5. **S27.05** — Match visible power-control equipment and its bracketed attachment to the structure.
6. **S27.06** — Inventory local radiator/thermal hardware and compare its deployed shape and mounting for the selected date.
7. **S27.07** — Route utility bundles around rotary interfaces with plausible attachment and clearance.
8. **S27.08** — Match joint metal, blanket covers, and exposed beams without uniform surface roughness.
9. **S27.09** — Inspect ring back faces, root joints, and the P5 connection for missing structure or mesh penetration.
10. **S27.10** — Compare a close orbit and a moving wide view; the joint stays concentric and the array roots remain visibly connected.

### S28 — S3/S4 truss and array joints

Starboard inner photovoltaic structure, rotary joint, array roots, and local thermal hardware.

Reference anchors: [R2: NASA · Integrated truss structure](https://www.nasa.gov/international-space-station/integrated-truss-structure/). Part-specific comparison evidence is pending.

1. **S28.01** — Match the section lengths, cross-sections, and placement between S1 and S5.
2. **S28.02** — Reconstruct the starboard-specific transition geometry and equipment distribution from references.
3. **S28.03** — Match rotary-joint ring diameter, thickness, covers, and its actual axis through the structure.
4. **S28.04** — Verify both array-root positions and beta-joint orientations using their channel identities.
5. **S28.05** — Match power equipment shapes and their support brackets at the correct structural bays.
6. **S28.06** — Inspect local thermal hardware, including its dated deployment and pipe connections.
7. **S28.07** — Match visible harness routing around the rotating interfaces without stretched or unsupported cables.
8. **S28.08** — Compare beam metal, joint housings, and insulated equipment under identical lighting to P3/P4.
9. **S28.09** — Inspect both sides of the rotary joint and the S5 interface for incorrect gaps and overlaps.
10. **S28.10** — Fly from the central truss past both array roots; the section must hold its silhouette without detail popping or joint wobble.

### S29 — P5 spacer truss

Port spacer frame, end interfaces, fixed cabling, and visible fittings.

Reference anchors: [R2: NASA · Integrated truss structure](https://www.nasa.gov/international-space-station/integrated-truss-structure/). Part-specific comparison evidence is pending.

1. **S29.01** — Match spacer length, cross-section, and its gap-setting role between P4 and P6.
2. **S29.02** — Reproduce the exact diagonal pattern and open spaces in matched side and end views.
3. **S29.03** — Match beam profiles and end-node sizes instead of using identical round rods.
4. **S29.04** — Check both end interfaces for aligned mating plates and continuous attachment to neighboring structures.
5. **S29.05** — Place any visible fixed brackets and utility fittings in their documented bays.
6. **S29.06** — Route cables along their reference paths with support spacing visible at close range.
7. **S29.07** — Inspect internal beam crossings; joined members need plausible nodes, and unrelated members must not interpenetrate.
8. **S29.08** — Match bare metal and insulated surfaces without exaggerated rust, scratches, or procedural grime.
9. **S29.09** — Compare the negative space inside the frame from four oblique angles, not just its outer bounding box.
10. **S29.10** — Move a camera along the spacer and through open sightlines; reject disappearing diagonals and flickering cable detail.

### S30 — S5 spacer truss

Starboard spacer frame, end interfaces, cabling, and visible fittings.

Reference anchors: [R2: NASA · Integrated truss structure](https://www.nasa.gov/international-space-station/integrated-truss-structure/). Part-specific comparison evidence is pending.

1. **S30.01** — Match spacer dimensions and placement between S4 and S6 using starboard references.
2. **S30.02** — Reconstruct the observed diagonal pattern and cross-bracing with correct open bay shapes.
3. **S30.03** — Match beam sections, corner nodes, and attachment-plate thickness at astronaut scale.
4. **S30.04** — Verify both end planes and their alignment with adjacent photovoltaic structures.
5. **S30.05** — Inventory local brackets and fittings rather than mirroring P5 without evidence.
6. **S30.06** — Match utility routing and cable support positions through the starboard spacer.
7. **S30.07** — Inspect beam junctions and internal crossings for impossible structural intersections.
8. **S30.08** — Compare metal highlights and local insulation with adjacent truss sections under common lighting.
9. **S30.09** — Check front, rear, underside, and end-on negative spaces against matched reference views.
10. **S30.10** — Fly along both edges and beneath the spacer; thin beams must remain continuous, stable, and correctly shaded.

### S31 — P6 outer photovoltaic truss

Outboard port structure, array roots, electrical equipment, and local radiator assemblies.

Reference anchors: [R2: NASA · Integrated truss structure](https://www.nasa.gov/international-space-station/integrated-truss-structure/); [R6: ESA · ISS radiators, Luca Parmitano photograph](https://www.esa.int/ESA_Multimedia/Images/2020/01/International_Space_Station_radiators2). Part-specific comparison evidence is pending.

1. **S31.01** — Match P6's full structural dimensions and placement beyond P5.
2. **S31.02** — Reconstruct its frame bays, equipment-bearing surfaces, and end geometry from multiple views.
3. **S31.03** — Verify both legacy array-root positions and orientations against their channel identities.
4. **S31.04** — Match local radiator outlines, panel divisions, and deployment state in the frozen configuration.
5. **S31.05** — Inspect radiator hinges, supports, and plumbing at their actual truss attachment points.
6. **S31.06** — Map electrical and battery equipment to the correct bays and reproduce distinctive covers.
7. **S31.07** — Match cable bundles, array-root fittings, and installed iROSA support interfaces without duplicate geometry.
8. **S31.08** — Compare radiator, insulation, beam metal, and electrical-cover materials under calibrated sunlight.
9. **S31.09** — Inspect the outboard end and underside for missing details hidden in station-wide photographs.
10. **S31.10** — Fly around the entire structure and between visible appendages; no panel intersections or thin-surface disappearance.

### S32 — S6 outer photovoltaic truss

Outboard starboard structure, array roots, power equipment, and local radiator assemblies.

Reference anchors: [R2: NASA · Integrated truss structure](https://www.nasa.gov/international-space-station/integrated-truss-structure/); [R7: NASA · Sixth iROSA installation, 15 June 2023](https://www.nasa.gov/blogs/spacestation/2023/06/15/nasa-spacewalkers-finish-installing-roll-out-solar-array/). Part-specific comparison evidence is pending.

1. **S32.01** — Match the outer section's dimensions and its connection beyond S5.
2. **S32.02** — Reconstruct the actual frame bays and equipment distribution from starboard-specific photographs.
3. **S32.03** — Verify both legacy array-root positions and the associated iROSA mounting locations.
4. **S32.04** — Match local radiator shapes, segmentation, and deployed geometry for the selected date.
5. **S32.05** — Inspect radiator mounting hardware and utility connections from the reverse side.
6. **S32.06** — Match battery and electrical hardware shapes, cover seams, and supporting brackets.
7. **S32.07** — Route cables through documented supports without crossing solar blankets or open mechanical joints.
8. **S32.08** — Match radiator coatings, insulation, exposed frames, and dark equipment apertures as distinct materials.
9. **S32.09** — Compare the outboard silhouette and underside structure with matched close and wide references.
10. **S32.10** — Sweep around the section and its array roots; reject floating equipment, disconnected radiators, and shimmering framework.

### S33 — Eight legacy solar-array wings

All eight wings: separate evidence for 1A, 1B, 2A, 2B, 3A, 3B, 4A, and 4B; ten checks per instance.

Reference anchors: [R2: NASA · Integrated truss structure](https://www.nasa.gov/international-space-station/integrated-truss-structure/); [R7: NASA · Sixth iROSA installation, 15 June 2023](https://www.nasa.gov/blogs/spacestation/2023/06/15/nasa-spacewalkers-finish-installing-roll-out-solar-array/). Part-specific comparison evidence is pending.

1. **S33.01** — Verify each wing's channel identity, host truss, side, and orientation in the station configuration.
2. **S33.02** — Match deployed length, total width, central mast, and blanket separation using dimensioned references.
3. **S33.03** — Reconstruct cell-grid proportions and blanket segmentation; a generic tiled checkerboard is a failure.
4. **S33.04** — Match the central mast, end bars, tension geometry, and root structure at close range.
5. **S33.05** — Inspect blanket thickness and edge silhouette without turning flexible blankets into thick rigid boards.
6. **S33.06** — Match front and rear surface appearance independently, including conductor and support patterns visible in sources.
7. **S33.07** — Verify the documented joint pose and clearance to adjacent wings, radiators, and iROSA overlays.
8. **S33.08** — Compare warm/cool color shifts and glints under matched light; reject neon orange paint or uniform metallic mirrors.
9. **S33.09** — Inspect grazing-angle motion for moire, aliasing, shadow acne, and unstable cell textures.
10. **S33.10** — Compare every complete wing from both sides and end-on; all eight must retain detail and connection continuity.

### S34 — Six iROSA wings and support kits

The six installed June 2023 wings on 2B, 4B, 3A, 4A, 1A, and 1B; separate evidence for every installation.

Reference anchors: [R7: NASA · Sixth iROSA installation, 15 June 2023](https://www.nasa.gov/blogs/spacestation/2023/06/15/nasa-spacewalkers-finish-installing-roll-out-solar-array/). Part-specific comparison evidence is pending.

1. **S34.01** — Verify the six correct channel locations and leave non-equipped channels free of invented installed wings.
2. **S34.02** — Match each roll-out wing's length, width, and relative footprint on the older array.
3. **S34.03** — Reconstruct the support-kit geometry and angle rather than placing a floating rectangle in front of a legacy wing.
4. **S34.04** — Match deployment booms, end structure, rolled-edge details, and root hardware from installation photographs.
5. **S34.05** — Reproduce the visible photovoltaic cell pattern at the correct scale and orientation.
6. **S34.06** — Match front/back appearance and edge thickness as separate observed surfaces.
7. **S34.07** — Trace power cables to their proper interfaces with attached connectors and supported routing.
8. **S34.08** — Check overlay clearance and shadow placement on the original array from several oblique angles.
9. **S34.09** — Inspect the full support kit from behind for disconnected beams, duplicate faces, and hidden intersections.
10. **S34.10** — Fly past each of the six installations; cell detail, thin booms, and contact shadows remain stable in motion.

### S35 — Canadarm2

Arm, both end effectors, cameras, blankets, joints, and its visible attachment in the chosen pose.

Reference anchors: [R8: CSA · Canadarm2](https://www.asc-csa.gc.ca/eng/iss/canadarm2/). Part-specific comparison evidence is pending.

1. **S35.01** — Match overall reach, segment proportions, and joint sizes to CSA specifications and photographs.
2. **S35.02** — Verify both end identities and the actual attached grapple fixture in the frozen reference pose.
3. **S35.03** — Match shoulder, elbow, and wrist bends across multiple views; do not accept a pose inferred from one silhouette.
4. **S35.04** — Reconstruct each joint housing, bearing gap, and mechanical connection with clean, concentric geometry.
5. **S35.05** — Match end-effector depth, opening, mechanisms, cameras, and local fittings at close range.
6. **S35.06** — Reproduce blanket seams, lettering, and their orientation along the separate arm segments.
7. **S35.07** — Check rigid-segment texture continuity and harness routing without stretching across joints.
8. **S35.08** — Compare blanket whiteness, exposed metal, dark lenses, and wear under the same lighting as the station.
9. **S35.09** — Inspect every joint underside and the base contact for collisions with the station or detached arm segments.
10. **S35.10** — Orbit from root to tip and compare a full-station view; the arm retains correct scale and clear silhouette throughout.

### S36 — Dextre

Torso, both manipulator arms, tools, cameras, and its dated mount/storage pose.

Reference anchors: [R9: CSA · Dextre](https://www.asc-csa.gc.ca/eng/iss/dextre/). Part-specific comparison evidence is pending.

1. **S36.01** — Match torso size, arm proportions, and overall envelope to CSA reference dimensions.
2. **S36.02** — Verify the selected mounting location and the mechanical connection to its carrier or arm.
3. **S36.03** — Match both arm poses independently, including shoulder, elbow, and wrist orientation.
4. **S36.04** — Reconstruct joint housings and the gap geometry that distinguishes articulated mechanisms from joined cylinders.
5. **S36.05** — Match tool interfaces and end mechanisms rather than terminating each arm in a featureless block.
6. **S36.06** — Place cameras, work lights, tool holders, and visible auxiliary equipment from a dated inventory.
7. **S36.07** — Match insulation seams, exposed structure, and recognizable markings at close approach distance.
8. **S36.08** — Inspect harnesses and mechanical attachments behind the torso and between the arms.
9. **S36.09** — Compare the front, rear, underside, and both sides for accidental self-intersection and missing equipment.
10. **S36.10** — Fly around the full robot against station and Earth backgrounds; fine tools must remain attached and temporally stable.

### S37 — Mobile Base System and Mobile Transporter

Platform, carriage, rail contacts, grapple fixtures, and fixed hardware; carried robots are scored separately.

Reference anchors: [R10: CSA · Mobile Base System](https://www.asc-csa.gc.ca/eng/iss/mobile-base/). Part-specific comparison evidence is pending.

1. **S37.01** — Match platform dimensions, height, and outline against CSA specifications.
2. **S37.02** — Verify its selected rail worksite and orientation along the integrated truss.
3. **S37.03** — Reconstruct the carriage's rail contacts and support geometry without a platform floating above the track.
4. **S37.04** — Match the four grapple fixtures, their orientations, mounting plates, and spatial arrangement.
5. **S37.05** — Inspect the payload support interfaces and visible hold-down hardware from close reference views.
6. **S37.06** — Match platform deck, framework, cable routing, and equipment boxes on both upper and lower faces.
7. **S37.07** — Check clearances to adjacent truss equipment and the carried robot in the frozen pose.
8. **S37.08** — Compare exposed structural metal, white covers, and dark mechanical regions under consistent light.
9. **S37.09** — Inspect the underside and wheel/rail region for duplicated tracks, missing contacts, and intersecting geometry.
10. **S37.10** — Fly along the rail and around the platform; grapple detail and carriage supports remain readable and stable.

### S38 — EXPRESS Logistics Carriers · ELC-1 through ELC-4

Every carrier, its individual payload manifest and mounting structure; all four assessed separately.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/). Part-specific comparison evidence is pending.

1. **S38.01** — Verify each carrier's identity, host truss, attachment face, and rotational orientation.
2. **S38.02** — Match each platform's outline, thickness, frame, and attachment geometry to photographs.
3. **S38.03** — Map occupied and empty payload positions independently for the frozen date.
4. **S38.04** — Reconstruct each carried unit's visible shape, proportions, cover seams, and orientation rather than generic box clutter.
5. **S38.05** — Match payload feet, restraint fixtures, and carrier interfaces so every unit has a visible supported attachment.
6. **S38.06** — Trace exposed utility connections and cables to the correct payload and carrier interfaces.
7. **S38.07** — Inspect every platform underside, edge, and support bracket in oblique views.
8. **S38.08** — Match blankets, radiator-like faces, metal frames, and dark apertures by payload instead of applying one shared finish.
9. **S38.09** — Compare platform silhouettes and clearance from nearby arrays, robots, and station structure.
10. **S38.10** — Fly around all four carriers; no hidden duplicate payloads, floating boxes, overlapping mounts, or unstable thin hardware.

### S39 — External Stowage Platforms · ESP-1 through ESP-3

All three platforms, their separate dated spare-equipment inventories, restraints, and supports.

Reference anchors: [R1: NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/). Part-specific comparison evidence is pending.

1. **S39.01** — Verify each platform's identity, location, mounting orientation, and attachment to its actual host.
2. **S39.02** — Match the individual platform outline, thickness, frame pattern, and support geometry.
3. **S39.03** — Inventory the stored units and empty attachment sites for the selected date.
4. **S39.04** — Match each spare unit's distinctive shape and dimensions; repeated generic crates fail.
5. **S39.05** — Reconstruct restraint and attachment hardware with visible contact between the stored unit and platform.
6. **S39.06** — Match protective covers, wrapped equipment, handles, and visible identification markings to photographs.
7. **S39.07** — Inspect rear surfaces, platform undersides, and narrow gaps between stored units.
8. **S39.08** — Compare bare structure, fabric covers, reflective insulation, and painted parts as separate materials.
9. **S39.09** — Check the complete stowage silhouette and clearance from nearby astronaut routes and station appendages.
10. **S39.10** — Perform a close flyby of every platform; reject unsupported spares, penetrating straps, missing back faces, and unstable edges.

### S40 — Alpha Magnetic Spectrometer · AMS-02

Instrument envelope, external thermal hardware, support structure, and equipment visible in June 2023.

Reference anchors: [R11: NASA · Alpha Magnetic Spectrometer](https://www.nasa.gov/alpha-magnetic-spectrometer/about-alpha-magnetic-spectrometer/). Part-specific comparison evidence is pending.

1. **S40.01** — Match the complete instrument's measured envelope and distinctive multi-part silhouette.
2. **S40.02** — Verify its mounting position and orientation on the starboard truss.
3. **S40.03** — Reconstruct the primary housing, top geometry, and exposed structural framework from multiple photographs.
4. **S40.04** — Match thermal panels and external radiator/support geometry, including visible reverse surfaces.
5. **S40.05** — Inventory external boxes, blankets, and changes present by the chosen date; launch configuration alone is insufficient.
6. **S40.06** — Match cable and cooling-line routes, connectors, and their supports without arbitrary dangling detail.
7. **S40.07** — Inspect the attachment structure and all load-bearing contacts with the station from underneath.
8. **S40.08** — Compare foil, white thermal surfaces, exposed metal, and dark apertures under calibrated illumination.
9. **S40.09** — Check its silhouette and clearances against neighboring payloads, truss members, and solar-array hardware.
10. **S40.10** — Orbit the complete instrument at close and medium range; layered covers and support members remain clean and stable.

## Additional acceptance gates

### A — Preserve the astronaut; add convincing animation

Reference anchors: [R15](https://3d.si.edu/object/3d/armstrong-space-suit%3Ad8c63ba6-4ebc-11ea-b77f-2e728ce88125).

1. **A.01** — Preserve the approved suit's silhouette, fabric, patches, visor, gloves, boots, and color. Compare the same ten baseline views before and after rigging; any visible loss requires correction.
2. **A.02** — Add an articulated skeleton with anatomically placed shoulders, elbows, wrists, hips, knees, and ankles. Inspect shaded and wireframe deformation at neutral and extreme allowed poses.
3. **A.03** — Make arms and legs visibly respond during movement, with restrained motion appropriate to a bulky pressurized suit; reject a rigid statue sliding through the scene.
4. **A.04** — Use gentle, asymmetric arm and leg drift at rest. Limbs settle smoothly after input stops, without synchronized pendulum loops or sudden resets.
5. **A.05** — Use a grounded stepping cycle only when feet have a supported contact surface; free flight uses floating poses, with no walking through empty space.
6. **A.06** — Keep fabric volume across bent elbows, shoulders, knees, and hips. Reject collapsing joints, torn seams, stretched patches, and candy-wrapper twisting.
7. **A.07** — Keep gloves attached at the wrist and boots attached at the ankle through the full pose range; no hand, sleeve, or knee passes through another suit surface.
8. **A.08** — Keep the backpack and helmet rigidly mounted while the body animates; neither may squash with skin weights or penetrate the torso.
9. **A.09** — Attach the tether to its visible suit fitting and update it through every pose. Inspect the front, rear, underside, and full camera orbit while moving.
10. **A.10** — Record forward, reverse, sideways, vertical, braking, idle, and turning sequences. Preserve appearance in motion and confirm the animated envelope stays clear of station geometry.

### C — Camera, movement, view buttons, and tether

1. **C.01** — Right-button drag orbits the camera independently around the astronaut through a full 360 degrees, including an unobstructed front/visor view and a visible tether attachment.
2. **C.02** — Right-drag changes neither body heading nor thrust direction. Suppress the browser context menu only on the game canvas; releasing the button leaves the chosen view in place.
3. **C.03** — Left-button drag turns the astronaut's body and its forward movement heading. WASD supplies translation; the camera follows continuously without sudden snapping.
4. **C.04** — Keep vertical movement and braking available with clearly displayed bindings. Translation, turning, and camera orbit must work in combination without stuck input.
5. **C.05** — Provide an explicit recenter control and bounded camera distance. Vertical orbit must not flip the image or pass through the astronaut's helmet and body.
6. **C.06** — Preserve the existing named view buttons and make their effects clear. Interior, EVA, station overview, and suit inspection must load a readable, unclipped composition.
7. **C.07** — Allow inspection around both ends, all sides, and beneath the entire station. Camera collision should slide or shorten smoothly without passing through structure or hiding the astronaut unnecessarily.
8. **C.08** — Keep the tether attached at both visible ends, routed around obstacles, and within its allowed length. Slack must not sag as if under Earth-surface gravity or pass through the suit.
9. **C.09** — Support a usable route around the station through tether reattachment/reeling and free movement as applicable. Test constrained corners, full extension, detachment, return, and recovery from obstruction.
10. **C.10** — Test button release outside the canvas, lost focus, simultaneous buttons, view switching, and reload. Controls must recover cleanly; use isolated Playwright self-play and captured visual evidence.

### E — Earth detail, clouds, atmosphere, and lighting

Reference anchors: [R12](https://science.nasa.gov/earth/earth-observatory/blue-marble-next-generation/base-map/).

1. **E.01** — Choose imagery by ground detail visible from the actual orbital altitude. A larger file or an 8K label does not pass: compare coastlines, terrain, and cloud edges at native 1080p and 1440p captures.
2. **E.02** — Use sufficient source detail and distance-appropriate tiles so close Earth views have no obvious square pixels or smeared continents. Upscaled low-resolution imagery alone fails.
3. **E.03** — Inspect tile boundaries, longitude wrap, poles, coastlines, and ocean/land transitions for seams, mismatched color, duplicate clouds, and blurred joins.
4. **E.04** — Build clouds as a separate altitude layer with convincing thickness, soft edges, and varied structure. Reject clouds painted onto the land or an opaque white shell.
5. **E.05** — Animate clouds slowly relative to the ground with regional variation and continuous motion; rotating one rigid cloud globe is insufficient for the requested improvement.
6. **E.06** — Show cloud motion in a time-separated comparison with ground landmarks tracked. At normal speed it is subtle; time acceleration must reveal continuous drift without a looping jump.
7. **E.07** — Match the thin atmospheric limb and horizon falloff to orbital photographs, using an actual altitude-to-radius relationship rather than an oversized neon halo.
8. **E.08** — Use one coherent Sun direction for Earth, clouds, station, and astronaut. Cloud shadows, land shading, and the day/night boundary must agree.
9. **E.09** — Match ocean darkness, land saturation, cloud brightness, and glint to exposure-matched references. Preserve cloud detail without crushed land or blown-out white surfaces.
10. **E.10** — Capture horizon, straight-down, sunset, and night-side motion. Reject cloud/ground intersections, texture swimming, unstable shadows, visible detail transitions, and excessive stars under daylight exposure.

### O — Real orbital motion and a stable playable station

Reference anchors: [R13](https://www.nasa.gov/international-space-station/space-station-facts-and-figures/).

1. **O.01** — Use metres consistently and record Earth radius, orbital altitude, inclination, and simulation time in the scene specification. The station's scale must remain 1:1.
2. **O.02** — Move the station's reference frame along an actual orbital trajectory around Earth; spinning the Earth texture under a stationary station alone fails.
3. **O.03** — Calculate orbital period from the chosen radius and gravitational parameter. Verify a complete simulated orbit against the calculation and the reference altitude, rather than hardcoding an arbitrary fast loop.
4. **O.04** — Advance Earth's rotation separately from the station orbit and cloud drift. Track a named ground landmark to demonstrate these motions are independent.
5. **O.05** — Keep the astronaut, station, active camera, and tether in a numerically stable local frame that follows the orbit together; no drift away from the station when controls are idle.
6. **O.06** — Use a documented station attitude relative to the orbit so Earth-facing views remain physically coherent. Compare the horizon direction from the Cupola and exterior views.
7. **O.07** — Keep Sun direction consistent through orbital motion; station shadows, illuminated array faces, Earth lighting, and eclipse timing must agree.
8. **O.08** — Offer clearly labeled real-time and accelerated orbital viewing. Acceleration changes simulation time consistently and must not secretly change astronaut movement speed.
9. **O.09** — Switch views, orbit the astronaut camera, and attach/reel the tether during accelerated and normal orbit. Reject jumps, precision jitter, length changes, or broken relative positions.
10. **O.10** — Record continuous normal-speed and accelerated sequences plus positions over one orbit. Require visible ground-track progression and correct shadow changes; a static screenshot cannot establish this gate.

### I — Interior fidelity and continuity

Reference anchors: [R3](https://humans-in-space.jaxa.jp/en/kibo/); [R4](https://www.esa.int/Science_Exploration/Human_and_Robotic_Exploration/Node-3_Cupola/ISS_and_Europe_s_Major_Contributions); [R14](https://www.nasa.gov/image-article/robotic-workstation-destiny-lab/).

1. **I.01** — Replace any invented straight corridor layout in explorable areas with the actual connected-module topology and measured hatch-center relationships.
2. **I.02** — Match interior cross-sections, passage widths, rack depths, and hatch sizes to the specific module; one corridor template repeated everywhere fails.
3. **I.03** — Build reference boards for every player-accessible interior wall and end, including the ceiling and areas behind the starting camera.
4. **I.04** — Match racks, storage bags, restraints, ventilation grilles, and labels by location and scale; equipment density must follow references rather than random clutter.
5. **I.05** — Attach cables, bags, panels, and equipment to visible supports. Inspect their back sides and every accessible gap for floating objects and intersections.
6. **I.06** — Use distinct textiles, coated panels, metal fittings, displays, and glazing. Match local illumination without flattening the cabin into uniform white or colored neon.
7. **I.07** — Preserve clean sightlines and astronaut clearance at actual scale; adjust navigation and animation instead of secretly widening the station.
8. **I.08** — Keep interior windows and exterior openings physically consistent, including frame thickness and the correct view of Earth or station equipment.
9. **I.09** — Allow the existing view-based inside/outside transition; door mechanics are optional. Arrival pose, camera clearance, controls, and tether state must remain coherent.
10. **I.10** — Record a continuous tour of every explorable interior area, looking at all walls and moving through each junction. No walk-through walls, clipped suit, missing ceiling, or exposed exterior shell.

### G — Whole-scene acceptance and non-regression

1. **G.01** — Compare full-station forward, aft, port, starboard, zenith, and nadir renders against the frozen configuration, then repeat matched oblique flyaround views. Wrong topology or a missing assembly blocks completion.
2. **G.02** — Maintain a host-and-child inventory for every visible component, including antennas, visiting vehicles, science payloads, brackets, and transferred hardware. Every item must belong to a rubric and have reference evidence.
3. **G.03** — Run named collision approaches against every major assembly and its protrusions, in both travel directions where reachable. Test the astronaut, animated limbs, camera, and tether separately.
4. **G.04** — Use native-resolution stills and moving captures at 1080p and 1440p. Inspect a screen grid for silhouette errors, blur, clipped details, floating objects, and excessive post-processing.
5. **G.05** — Keep normals, tangents, triangulation, glass ordering, shadows, texture filtering, and detail transitions stable. Zero reproducible visible cracks, exposed intersections, flicker, or missing back faces are allowed on reachable views.
6. **G.06** — Use a recorded reference device/browser/settings profile. Proposed performance gate: median at least 60 FPS, p95 frame time at most 22 ms, and p99 at most 33.3 ms on each warmed 120-second 1080p traversal. Report 1440p separately.
7. **G.07** — Measure complete traversals around arrays, radiators, robotics, interiors, Earth, and the animated suit. No traversal may be represented by an empty-scene or stationary-camera benchmark.
8. **G.08** — Record cold-load time, asset bytes, memory, loading failures, and console errors. Required assets must load, no fatal errors are allowed, and warmed movement must have no asset-loading freeze over 100 ms.
9. **G.09** — Compare every candidate with the accepted baseline at identical cameras, lighting, settings, and motion. Improvements cannot conceal regression in the approved suit, input, clarity, collision coverage, or performance.
10. **G.10** — Accept only the exact built version represented by the complete evidence ledger. Publish or hand over a final-quality claim only after all required checks pass; list remaining defects explicitly on any requested interim preview.

## Requested branding criterion

B.01 — Authentic OpenAI blossom on both astronaut and ISS: preserve the official mark proportions and orientation; place it on a physically attached suit patch and a station plaque; preserve existing mission badges; keep both legible at inspection distance with matching surface material, clean edges, no mirroring, no floating, clipping or flicker in all reachable angles and animated poses. Record separate suit and station evidence; both must pass. These requested marks are intentional artistic additions, not historical ISS or NASA branding.

## Reference register

These are starting references, not a completed photo survey. Older sources describe construction only until their dated configuration has been reconciled. The proposed six-iROSA date is anchored by NASA’s 15 June 2023 completion report.

- **R1** [NASA · Station assembly elements](https://www.nasa.gov/international-space-station/international-space-station-assembly-elements/) — Assembly names and dated installation history. Individual dated close-up photographs still need to be selected for each check.
- **R2** [NASA · Integrated truss structure](https://www.nasa.gov/international-space-station/integrated-truss-structure/) — Truss organization and reference entry point; appendage pose requires dated imagery.
- **R3** [JAXA · Kibo](https://humans-in-space.jaxa.jp/en/kibo/) — Japanese laboratory reference entry point. Archive diagrams must be checked for equipment no longer present.
- **R4** [ESA · European contributions](https://www.esa.int/Science_Exploration/Human_and_Robotic_Exploration/Node-3_Cupola/ISS_and_Europe_s_Major_Contributions) — Useful historical module reference; future-tense launch descriptions do not establish the June 2023 configuration.
- **R5** [ESA · European Robotic Arm](https://www.esa.int/Science_Exploration/Human_and_Robotic_Exploration/International_Space_Station/European_Robotic_Arm) — Arm description and specifications; use on-orbit photographs to select its pose.
- **R6** [ESA · ISS radiators, Luca Parmitano photograph](https://www.esa.int/ESA_Multimedia/Images/2020/01/International_Space_Station_radiators2) — Close radiator construction reference, photographed in 2019. Confirm pose separately for the scene date.
- **R7** [NASA · Sixth iROSA installation, 15 June 2023](https://www.nasa.gov/blogs/spacestation/2023/06/15/nasa-spacewalkers-finish-installing-roll-out-solar-array/) — Dated anchor for the proposed six-iROSA station configuration.
- **R8** [CSA · Canadarm2](https://www.asc-csa.gc.ca/eng/iss/canadarm2/) — Official specifications and image/video entry points.
- **R9** [CSA · Dextre](https://www.asc-csa.gc.ca/eng/iss/dextre/) — Official robot reference and image/video entry points; exclude later upgrades from the chosen scene.
- **R10** [CSA · Mobile Base System](https://www.asc-csa.gc.ca/eng/iss/mobile-base/) — Platform, rail-car relationship, and dimensional reference.
- **R11** [NASA · Alpha Magnetic Spectrometer](https://www.nasa.gov/alpha-magnetic-spectrometer/about-alpha-magnetic-spectrometer/) — Instrument reference; external service changes need dated photographs.
- **R12** [NASA · Blue Marble base-map source tiles](https://science.nasa.gov/earth/earth-observatory/blue-marble-next-generation/base-map/) — 500 m source tiles are a candidate for sharper land imagery; this is historical imagery, not live weather or proof of final visual quality.
- **R13** [NASA · Station facts and figures](https://www.nasa.gov/international-space-station/space-station-facts-and-figures/) — Orbital context; the simulation must use explicitly recorded values rather than imply live ISS tracking.
- **R14** [NASA · Destiny robotics workstation](https://www.nasa.gov/image-article/robotic-workstation-destiny-lab/) — Interior layout and equipment reference for the photographed area, not an entire-interior reconstruction.
- **R15** [Smithsonian · Armstrong spacesuit scan](https://3d.si.edu/object/3d/armstrong-space-suit%3Ad8c63ba6-4ebc-11ea-b77f-2e728ce88125) — Approved historical suit appearance is retained by request. The avatar is an explicit artistic exception to a period-accurate ISS crew suit.
- **R16** [NASA · ISS(C) high-resolution 3D model candidate](https://science.nasa.gov/3d-resources/international-space-station-iss-c-high-res/) — Candidate to inspect after review. A NASA model or high-resolution label does not automatically pass the geometry, date, texture, or close-up checks.

## Evidence row template

Check ID | Child instance | Build ID | Reference IDs and date | Camera and light | Screenshot or clip | Measurement | Score | Status | Defect and retest

Initial status for all rows: Unreviewed. No implementation or quality claims are implied by this document.