Microchannel Cold Plates
Thermal flux of 100–300 W/cm² over high-density GPU/ASIC arrays via a synthetic obsidian interface.
Unlocking Terawatt-Scale Orbital AI Compute with Next-Gen Radiative Cooling
Powering orbital AI constellations with high-emissivity deployable radiators (ε ≥ 0.95), MPTL two-phase fluid loops, and space-qualified thermal architectures.
Orbital Applications
Low Earth Orbit (LEO) Data Centers
Massive supercomputing infrastructure for processing LLM models and computer vision directly in space.
Orbital Applications
Terrestrial Edge Processing
Drastic reduction of latency and bandwidth by processing and filtering satellite imagery in real time before transmission.
Orbital Applications
Commercial Space Stations
Standardized cooling modules for laboratories and critical infrastructure in interplanetary missions and lunar bases.
Terrestrial Data Center vs. Itztli Orbital Thermal Module
| Metric | Terrestrial Data Center | Itztli Orbital Module |
|---|---|---|
| Water Consumption | Millions of L/year | 0 liters (radiative dissipation to vacuum) |
| Energy Overhead | 30%–40% (terrestrial PUE) | <2% (parasitic pumping) |
| Mission Scalability | Fixed ground infrastructure | 1 kW–20 kW (SmallSats Edge) → 300 kW+ (Starship payloads) |
| Readiness Level | TRL-9 (mature) | TRL-6 / TRL-7 qualification path |
About Itztli
"Inspired by Itztli, the Mexica deity of obsidian and piercing cold, we create the precision engineering that masters the thermal fire of AI on the space frontier."
Comprised of thermal engineers, fluid dynamics specialists, and aerospace flight qualification experts.
Thermal Challenge in Orbit: Deep Vacuum Physics
The Challenge
With no air or water in 0-g, dissipating more than 250 kW per satellite requires transferring heat exclusively by infrared radiation into the cosmic vacuum (T_sink ~ 3 K).
The Solution: Two-Phase (2Φ) Loops
Mechanically pumped two-phase loops exploit the latent heat of vaporization with parasitic energy consumption below 2%.
Technology Pillars: Verified Specifications
Active MPTL Loop
Mechanically Pumped Two-Phase Loop with 10⁻⁹ mbar·L/s hermeticity, designed for +10-year missions in LEO/SSO.
Deployable Radiator Panels
Radiative emissivity ε ≥ 0.95 and solar absorptivity α ≤ 0.09 using carbon nanotubes and Optical Solar Reflectors (OSR).
Space Hardening
Thermal cycling resistance from −150 °C to +120 °C, Atomic Oxygen (AO) passivation, and micro-meteoroid shielding.