Spacecraft Thermal Modeling — Vertex Aerospace
Three flight systems modeled in Thermal Desktop
- ~110°C
- Peak temp reduction
- 25°C
- Held through eclipse
- 3
- Spacecraft systems
Problem
In orbit a spacecraft swings between intense direct sun and cold eclipse, and every component has an operating band it must hold through both. Three systems needed thermal designs that stayed in band across the full orbit.
Motivation
As a thermal engineering intern at Vertex Aerospace, I owned the modeling for three spacecraft systems — work that fed directly into designs reviewed and approved by senior engineers.
Constraints
- Components had to stay within limits from direct-sun hot cases through eclipse cold cases
- Radiators and heaters sized within the systems' mass and power budgets
- Results had to withstand senior-engineer design review
Process
- 01
Modeling
Built transient thermal models of three spacecraft systems in Thermal Desktop, applying emissivity and absorptivity properties through Stefan-Boltzmann analysis.
- 02
Optimization
Tuned radiator and heater configurations to hold components in band — decreasing direct-sunlight temperatures by up to ~110°C while maintaining 25°C through eclipse.
- 03
Communication
Rendered transient simulation results and orbit animations on the CAD models to communicate thermal-system effectiveness to reviewers.
Key decisions
Radiator sizing paired with active heater control
Why · Radiators alone overcool through eclipse; pairing them with heaters held the operating band across both extremes of the orbit without over-massing the system.
Results
- ✓Up to ~110°C reduction in direct-sunlight component temperatures.
- ✓Maintained 25°C through eclipse cold cases.
- ✓Thermal models for three systems reviewed and approved by senior engineers.
Lessons learned
- Thermal design is a balancing act between hot and cold cases — solving one can break the other.
- Clear visualization is what makes analysis trusted in review.