Abstract
To meet the thermal insulation requirements of the measurement system in the liquid oxygen tank of the rocket, we designed the thermal insulation structure of the optical measuring device at an extremely low temperature based on phase change temperature control, selected neicosane as the phase change material, and used 15 mm phase change layer to combine with 9 mm polyurethane thermal insulation layer to achieve passive temperature control. Finally, a thermal simulation model is established for transient thermal analysis. The simulation results show that the internal temperature of the system decreases from the initial temperature of 50 °C to -13.9 °C after 2 hours, which proves that the design meets the requirements.
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