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Increasingly demanding space-based applications require a large primary mirror diameter, on which the optical instrument resolution depends. However, the mass and volume of a monolithic primary mirror would dramatically increase along with its size, which, in addition to cost and technical issues, is also limited by the available volumen in the launch vehicle fairing.

A GSTP De-Risk Framework with RUAG Space Germany designed and demonstrated a novel, compact and robust sensor head for angular sensors for space mechanisms, using modern and advanced materials and manufacturing methods.

The final performance tests provided evidence in terms of high precision manufacturability of ceramic packages.

The robust design was found to be suitable for the harsh space environment

Currently, the Loop heat pipe evaporators are mainly cylindrical in order to cope with the internal working pressure. All electronic units have a flat thermal interface. This means that an LHP requires an thermal interface adaptor from a rectangular flat surface to a cylindrical shape (e.g. saddle). Therefore, these additional thermal interfaces and the small contact area decrease the overall performance of the Loop heat pipe.

This study aimed to demonstrate the feasibility, use and functionality of carbon fibre-reinforced flexible epoxy (CFRFE) materials for self-deployable space structures (such as deployable tape-spring hinges) by designing, simulating, manufacturing, testing and correlating a classic (100% carbon fibre-reinforced plastic -rigid resin- CFRP) deployable tape-spring hinge and a CFRFE deployable tape-spring hinge and compare their mechanical and dynamic behaviours.

Achievements and status: Space applications: 10 Space applications identified. 2 Space applications assessed with ESATAN Derivation of requirements: Development requirements have been established and demonstrator requirements derived. Investigations freezing point depression: Molecular Dynamics Simulations and DSC Breadboard Tests have shown, that freezing point depression according to Gibbs Thomson is not feasible in the required scale. Thermal Performance Test: Phase Change could not be clearly detected.

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