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Using GNSS and Big Data Techniques to improve safety in critical maritime operations

This project was intended to contribute to the implementation of the e-navigation concept (as defined by IMO, Ref. 2.2.6), with primary focus on the navigation in restricted waters, such as harbours, lagoons or regions where the traffic congestion can create conditions for accidents or inefficient operations.

Italy

15/114

SATE
Environmental aspects of passive de-orbiting devices

The technical objective of this study was to understand the net effect of using deorbiting technologies like sails or tethers over the future debris population around Earth. In principle, indeed, these attractive technologies will support the compliancy to post-mitigation disposal guidelines, for small missions. However, the increased cross section also increases the collision risk.

Italy

15/095

Politechnico di Milano
Spacecraft tracking implications on operations and design of small satellites

Recent trends in miniaturisation of space hardware combined with the provision of affordable and standardised spacecraft components and structures is opening up space to new players and is rapidly increasing the traffic into orbit.

Italy

15/038

Telespazio
Powering rovers by High Intensity Laser Induction on Planets (PHILIP)

The scope of this study was to investigate the possibility of designing a wireless power transfer system from the lander to the rover, based on laser technology, to:

  • Avoid the use of nuclear power systems, such as the plutonium Multi Mission Radioisotope Thermoelectric Generator (MMRTG) accommodated onboard the NASA/JPL MSL Curiosity Rover, due to the constraints imposed by the use of radioactive materials

Italy

15/023

Leonardo
Mission performance assessment for space science missions

The objective of this activity was to propose a general infrastructure of an end-to-end simulator (E2ES) for space science missions, namely an E2ES requirements baseline, reference architecture and an associated library of software models (building blocks, BB) to promote reuse, standardisation and reduction of engineering costs by defining a products/science validation process throughout the lifecycle based on an E2ES.

Italy

16/S10

University of Trieste
M4 Phase A/B1 XIPE PHASE A

XIPE is designed to be launched with a VEGA-C vehicle into an orbit of 550 km and <6° inclination. With this orbit, eclipses last about 35 minutes. Due to remaining spacecraft fragments the mission is planned to end by controlled re-entry. The baseline ground station is Kourou either for S/S or S/X telemetry band, albeit Malindi (or Singapore) is additionally available, if necessary, for additional downloading capability in case of particularly bright sources. The mission duration is 3+2 years.

Italy

15/M23-a-2

Thales Alenia Space
Multi-purpose Cubesat at the ISS

The CubISSat study investigates the feasibility of operating a multi-purpose small satellite in the International Space Station (ISS) environment whose aim is to provide the ground and flight crew with effective tools to cope with a variety of situations, potentially avoiding to rely on complex robotics and extravehicular activities as currently conceived.

Italy

15/709-a

TYVAK INTERNATIONAL S.R....

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