In the context of space missions, effective thermal management is a crucial part for mission success. It is not only critical to ensure optimal payload performance but also for reliability of their subsystems. 

All components in a spacecraft must have a range of temperature requirements that must be respected to ensure proper functionality and integrity, which itself is a complicated matter in space, as temperature fluctuations occur very rapidly and drastically. To ensure thermal equilibrium in the subsystems of the spacecraft, systems temperatures are regulated by passive/active thermal control technologies.

In collaboration with Aistech Space, this thesis presents a study on the development and optimization of a Payload Thermal Control Subsystem (PTCS) of an advanced high-resolution (HR) thermal infrared (TIR) telescope.

The study aimed to analyze the thermal behavior of the subsystem and explore possible improvements of performance. Given the telescope’s demanding operational environment, combined with the strict requirements of thermal stability, an in-depth study and evaluation of the current thermal system was needed.

To achieve this, a series of thermal simulations and experimental tests were performed to develop a simulation model that accurately mirrored the actual system. This model was essential for iterating effectively on the design and analyzing the impact of the modifications on the system.

The work presented here resulted in the identification of the key factors affecting the thermal performance of the telescope as well as the design modifications needed to match the thermal requirements of the telescope.