THERMAL DRIFT LEDGER

Patrol Officer Ahmed Jacobs • Columbus Division • Orbital Adaptation Unit

Unit: W/(m·K) | Source: Wikidata Q487005 | Status: ACTIVE DEPLOYMENT

I. CORE EQUATION

q = k × (ΔT / d)

Heat flux density equals thermal conductivity times temperature gradient over distance. This is not poetry. This is the equation that determines whether the dome breathes or suffocates.

Columbus baseline: Winter delta-T = 47°C (−23°C to +24°C). Mars solstice delta-T = 112°C (−125°C to −13°C).

II. MATERIAL SPECIFICATIONS

Material Conductivity k [W/(m·K)] Density [kg/m³] Application Layer Columbus Test
Regolith Sinter 0.02–0.08 1,800 Primary Shield (50cm) Pending
Silica Aerogel 0.014 150 Interlayer Buffer (10cm) Short North Lab
Kevlar Composite 0.04 1,440 Structural Mesh Verified
Borosilicate Glass 1.1 2,230 Viewports Active Duty
Aluminum 6061 167 2,700 Frame Members Standard Issue
CRITICAL: Aluminum frames create thermal bridges. Without aerogel isolation, heat loss spikes 340% at viewport junctions. Every weld is a potential breach.

III. PROTOTYPE VISUALIZATION

NASA Simulated Spacecraft Flight Facility prototype structure
SSPF - 25 Year Anniversary Test Structure. Kennedy Space Center. Public Domain. This is the architecture we inherit.

IV. FIELD CALCULATIONS

Target Flux Density
0.024
W/cm² max
Min Wall Thickness
52
cm composite
Max Temp Gradient
112
°C differential
Drift Tolerance
±0.003
W/(m·K)

These numbers were pulled from the Columbus winter patrol logs and scaled for Martian conditions. Deviate by 0.1% and the life support system enters emergency mode.