In 2009, the Nanosat study recommended a high degree of integration between data handling, AOCS and power distribution. Meanwhile, industry has come with innovate solutions where AOCS sensors are miniaturised and can be progressively introduced fully or partially in the central processor, typically coarse gyros, GNSS receivers or the processing part of the Star Trackers, leaving only optical heads or GNSS antennas to be accommodated as external units.

This activity was aiming to support in-orbit demonstration mission for the validation of ram electric propulsion technologies. It shall provide a plan for the development of an intake system for air-breathing thrusters.

We have continued our shock physics code calculation studies of DART-like impact events. This includes comparisons of iSALE and SPH code calculations, using a range of strength and structural properties. The effect of porosity was studied in detail by applying different crushcurves, representing materials with varying crushing strength. The crushcurve was found to have a large influence on the outcome, in particular the ejecta properties and momentum transfer.

In an era of high resolution gravity field modelling the dominant error sources in spacecraft orbit determination are non-conservative spacecraft surface forces, such as: Solar Radiation Pressure, antenna thrust, Earth' albedo, thermal re-radiation, etc. The conventional approach to these problems is to use an empirical blind model which absorb all the forces but this approach introduces systematic errors and limit the prediction of the orbit. In the last years several wind-box model have appeared, developed based in GPS and Glonass official information, to overcome this limitation.

In an era of high resolution gravity field modelling the dominant error sources in spacecraft orbit determination are non-conservative spacecraft surface forces, such as: Solar Radiation Pressure, antenna thrust, Earth' albedo, thermal re-radiation, etc. The conventional approach to these problems is to use an empirical blind model which absorb all the forces but this approach introduces systematic errors and limit the prediction of the orbit. In the last years several wind-box model have appeared, developed based in GPS and Glonass official information, to overcome this limitation.

The challenge of the Miniaturized transceiver design is, to design a new generation of TT&C
transceivers that can be efficiently configured and adapted to meet the requirements of a
diversity of both small and classical Hi-Rel missions. The new concept developed breadboard
validates the overall concept as well as the key new elements introduced. This activity drove a
design oriented to the new small platforms that will require this kind of products.

The Space4Maritime.gr study identified, analysed and prioritised via desk research, interviews and an online survey 118 unique needs of the maritime sector in Greece which could benefit from space infrastructure. It then translated these needs into a list of user requirements.

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Humankind tested its capacity to survive on the Moon’s surface for short periods of time through the Apollo missions almost 50 years ago. Since then, robotic missions to the Moon have spent periods lasting several days and nights on the satellite. However, many technological challenges arise when planning a lunar (robotic and/or manned) mission that is fully operational during the night. Among these challenges, the need for a power supply system for both day and night remains open.