Speaker
Description
Setting up a clean scenario for space management, where space debris are effectively removed from orbit following a design-to-demise strategy presents a formidable challenge. This involves employing design tools commonly developed and used for Thermal Protection System (TPS) of reentry vehicles. However, designing for space debris demise introduces a higher level of complexity, requiring engineers to adhere to much more stringent criteria and account for additional physical phenomena.
Several codes have been developed to initiate the design process and establish preliminary parameters for space debris demise. Nevertheless, these codes necessitate further consolidation and validation to ensure their efficiency and accuracy in real-world scenarios. To accomplish this, experimental test cases must be meticulously addressed to simulate the intricate conditions of reentry and assess the performance of satellite designs under such circumstances.
Central to this exploration is the identification and utilization of ground facilities capable of providing relevant testing conditions for evaluating spacecraft demisability. The selection of appropriate test facilities and test conditions are pivotal in accurately determining the effectiveness of engineering solutions designed to facilitate the controlled demise of space debris.
The present study aims to identify the capacities and the limits of aerospace ground testing facilities to realize destructive testing of typical satellite equipment. It will be the occasion to present how much high-enthalpy and plasma wind tunnels could offer full scale testing in full reentry conditions. Following this first analysis ground testing strategies for space debris re-entry duplication will be assessed for destructive testing of spacecraft equipment. The conclusion will open the discussion on the dedicated validation framework needed to properly consider experimental data and D4D tools.
