Analysis of an Active Thermal Control System for the Avionics Equipment for Future Upper-Stages of a Launcher System

Abstract

The main challenge of the avionics system in space launch vehicles is the control of the heat distribution. For a long time space missions have applied cost-effective passive solutions, chosen for their reliability on most applications. However, they add significant mass and have difficulty handling transient loads. The use of active thermal control systems such as Mechanically Pumped Fluid Loop (MPFL) has shown promising results for its implementation in past space missions. The present work presents an innovative design in the distribution of the avionics equipment on plates that together form a ringlike structure.