The thermal control design of space products is fundamentally different from that of ground equipment. In a vacuum environment, there is no conventional convective heat transfer — heat is primarily transferred through conduction and radiation balance. As a result, the thermal control system often determines whether the entire vehicle's electronics, payloads, and structural components can operate stably on orbit over the long term.
Industry Characteristics
- Complex external heat flux environment, jointly influenced by solar irradiation, Earth albedo, and infrared radiation
- Orbital period variations cause periodic temperature fluctuations
- High electronic equipment integration density, with pronounced local hot spots
Typical Simulation Content
- Whole-satellite steady-state and transient temperature field analysis
- Configuration assessment of heat pipes, radiator panels, and multilayer insulation materials
- Temperature response analysis under payload power-on/power-off conditions
- Structural thermal deformation assessment under different boundary conditions during launch and on-orbit phases
Recommended Approach
It is recommended to first build a system-level thermal network model for rapid orbital load-case screening; then establish refined models for satellite-borne electronic enclosures, optical payloads, and sensitive structures to verify thermal safety margins under extreme conditions. For high-precision payloads, pointing errors and alignment deviations caused by thermal deformation should also be evaluated in parallel.
Expected Benefits
By front-loading thermal control simulation, heat dissipation paths and temperature control strategies can be determined earlier, reducing the risk of late-stage layout changes and improving the first-pass success rate of whole-satellite thermal balance testing.