SIDLOC (Spacecraft Identification and Localization) is a new transmission scheme proposed by Libre Space Foundation to enable LEO satellite identification and tracking. The SIDLOC system relies on a reduced size autonomous transmitter that requires minimal integration and area on the carrier spacecraft. The ground segment of the SIDLOC system utilizes the existing SatNOGS network and the UHF band to perform the signal demodulation and identification. The SIDLOC system uses DSSS (Direct Sequence Spread Spectrum) PSK modulated signals with an effective bitrate of ~50 bits/s.

An Operations Ground Segment consists of a complex system of systems, each of which is a source of high-throughput events e.g. telemetry, Out-Of-Limits, operating/data/network system logs. Today the majority of MC systems support a particular subsystem, have limited processing / analysis capabilities (e.g. limit checking, synthetic parameters, filters) and support only stateless operations.

The main objective of this activity was to design and develop an innovative virtual lab for Mars experiments, where AI methods are used to improve orbital imagery resolution, as well to obtain terrain features based on local images from rovers. Two different methods were used to recreate the virtual environment. The first one was dedicated to process low resolution images from orbital information. The main contribution in this sense was the use of AI to increase the resolution of these images.

AbC is a compact on-board algorithm, initially intended for CubeSats, to measure the absolute direction of a distant beacon with optimised accuracy. The AbC environment anticipates a ground pipeline that has been used with OPS-SAT images to diagnose the ADCS. It has been shown that a ground-truth assessment of the satellite's orientation can be made which, with sufficient data, could allow precise re-alignment of multiple sensors. The ESA contract funded the implementation of the on-board algorithm in C++ and its pipeline in Python.

The AERODEM is an ESA demonstration mission that will implement an aerocapture phase in order to provide an atmospheric ∆V instead of a standard chemical one for orbiting a SpaceCraft around Mars. The aerocapture technique currently studied relies on a discrete event drag modulation technique that modifies only once the aerocapture module ballistic coefficient by separating / retracting the heatshield.

An interplanetary probe must decelerate from a hyperbolic interplanetory trajectory to an orbital trajectory when it arrives at its destination. Currently, this maneuvre is achieved using chemical propulsion, which means that propellant makes up a significant fraction of the vehicle mass. Aerocapture is an alternative concept that instead uses aerodynamic drag from the athmosphere of the planet to decelerate the arriving spacecraft.