System for space materials evaluation in LEO environment

Abstract

This paper describes the conception and experimental setup of a new concept for a Vacuum Ultraviolet with extreme Thermal Vacuum Cycle system and the evaluation of LEO satellites materials with the equipment. The system was developed in the framework of a study of spacecraft debris generation due to satellites materials degradation, when exposed to space environment. The study was developed in the framework of an ESA project. Its main purpose was to evaluate the characteristics and the quantity of debris resulting from surface of satellites due spacecraft materials degradation and provide input to space debris models. The experimental setup developed partially simulates the space environment, on an accelerated mode, as endured by a spaceship in Low Earth Orbit, allows the testing of materials to a Vacuum, Ultraviolet and thermal cycles. This thermal cycling provided to the sample holder was implemented using an innovative mechanical thermal switching architecture. This architecture allows temperature cycling of +200 °C to −200 °C without the use of LN2. The experimental setup design, manufacture and final characterization is presented.