Centradiant Space Systems

The thermal unlock for orbital computing.

The Problem

Orbital data centers are coming. SpaceX, Starcloud, Google, and others are racing to deploy compute in space. But heat dissipation in vacuum remains the fundamental scaling constraint. Traditional radiators mass 25-35 kg/kW(th), making large-scale orbital compute economically impossible.

The Solution

Centradiant's spinning disk liquid droplet radiator uses centrifugal collection to achieve 4.1 kg/kW(th), 6-9x lighter than state of the art. By using centrifugal force for droplet collection, we eliminate the electromagnetic systems that blocked LDR deployment for 30 years.

Key Numbers

Metric	Value
Radiator specific mass	4.1 kg/kW(th) (conservative)
Total spacecraft mass	916 kg launch / 796 kg dry
Heat rejection	55 kW thermal
Compute payload	64 GPUs (H100/B200), 44.8 kW
Disk radius	10 m, 2 RPM (0.045g at rim)
Working fluid	CB-DC705 (DC-705 + 100 ppm carbon black)
Parasitic power for collection	Zero
Capture efficiency	>99.99% per cycle

Mass Budget Summary (from V3_mass_rollup.py)

Subsystem	Mass (kg)
LDR disk (mesh, structure, spokes, rim)	219
PCHE heat exchanger	30.1
CB-DC705 fluid (120 kg inventory)	120
Galinstan rotary thermal joint	26.6
Solar array (145 m²)	218.5
Compute module (64 GPU + 8mm Al shield)	118.9
Bus, ADCS, comms	63
Dry mass	796
Propellant (5-year VLEO station-keeping)	120
Launch mass	916

Interactive Demo

3D Interactive Model: spinning disk with droplet physics, component info

Patent Portfolio

48 claims (8 independent) covering the centrifugal disk LDR architecture.

Figure	Description
Fig. 8	System overview
Fig. 9	Cross-section: droplet flow path
Fig. 10	Rim collector detail
Fig. 11	Hub, PCHE, and thermal rotary joint
Fig. 12	Spacecraft integration layout
Fig. 13	Energy flow block diagram

Engineering Analysis

35 analysis scripts in analysis/, all Python 3 stdlib only.

Key scripts: V3_mass_rollup.py, V3_final_budget.py, V3_executive_summary.py, V3_viability_roadmap.py, V3_ground_prototype.py, V3_regulatory_path.py

Repository Structure

├── README.md                        ← You are here
├── DESIGN-V2-SYNTHESIS.md           Authoritative design reference
├── D3-RISK-ANALYSIS.md              Comprehensive risk analysis
├── analysis/                        35 analysis scripts (Python 3, stdlib only)
├── patent/
│   ├── CLAIMS-OUTLINE.md            48 claims (8 independent)
│   ├── INVENTION-DISCLOSURE.md      Full invention disclosure
│   ├── PRIOR-ART.md                 Prior art analysis
│   ├── FILING-GUIDE.md              Patent filing instructions
│   ├── figures/                     6 D3 patent figures (SVG)
│   └── animation/                   Interactive demo
├── website/                         Astro + Tailwind site (centradiant.space)
└── archive/                         Legacy D1/D2 files (preserved for reference)

Business Case

Hybrid revenue: $12.6M/yr per satellite (DoD lease + platform + spot)
Ground prototype: $237K, 6 months to TRL 5
Entry path: SBIR(2027) → OTA(2028) → Pathfinder(2029) → Fleet(2031+)
Breakeven at $6.20/GPU-hr with B200 + Starship (2029)

Status

All 5 top engineering risks resolved. 35 analysis scripts validate every subsystem. Patent portfolio prepared (48 claims, 8 independent). Ground prototype program defined ($237K, 6 months). Seeking partners for hardware development.

Centradiant Space Systems, Walter Kueffer, Inventor

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