In 50 years of Space Exploration, the total distance covered by rovers on Mars and the Moon is about 200km, an average of 4km per year. Future exploration rovers are expected to travel one or two orders of magnitude more.This requires designing rovers that are intrinsically faster than what has been built so far.

The aim of the work has been to develop an efficient and robust turbine demonstrator that can efficiently operate under Mars environmental conditions. A combination of low friction and high inherent triboelectric charge density materials have been integrated into the Triboelectric Generator (TEG) architecture operating under a freestanding mode and including 4 generators. Each generator is compounded by Al+PTFE stator and H-DLC+Al rotor and the complete efficient design has 2 rotors and 4 stators.

Accurate localisation of assets on planetary bodies will be crucial in future exploration missions when it comes to autonomous vehicles navigation and accurate positioning. On Earth, dedicated systems in L-band are typically used for navigation and localisation.

Several SAR future Earth Observation missions requires large reflector antennas generating highly directive overlapped beams. This has been done so far with high power waveguide Beam Forming Networks including ferrite switches as implemented for Core H2O pre-developments. In this activity, it is proposed to investigate reflector antennas fed by overlapped subarrays. This represents an extremely promising concept for on-board SAR instruments.

Microbial contamination is a generic risk concerning flight hardware degradation, Planetary Protection and potentially crew health. Material surface requires a proper control and monitoring of the microbial cleanliness level. Today, contact plates, swabs and wipes are used for surface sampling. Swabs and wipes samples include mandatory liquid transfer to further extract and detect microorganism. Today, automated miniaturized system, molecular-based, has been developed and offers the possibility to perform multiple laboratory functions on a complete integrated system (i.e.

Assembly, Integration, and Testing (AIT) processes occur during the phases C and D of the engineering processes of a given flight vehicle. System integration processes take place at the level of engineering models, structural and thermal models, and qualification models of flight vehicles.The current ATD tools cover the phases 0, A, and part of the phase B (B1) for design, and development of flight vehicles. Beyond those phases, the current toolset is not able to cover tasks of system integration and testing (phases C, D).

OOne important constraint in the sizing process of an ablative TPS for atmospheric entry vehicles is the temperature limit of the supporting heatshield structure and of the bonding material used to attach the TPS. This temperature limit is typically in the range of 150-180degC. For the CFRP the limiting factor is typically the resin. New resin materials (like cyanate ester or bismaleimide) have commercially become available in recent years and relevant CFRP materials been qualified towards higher temperature limits for other space applications (like solar arrays or antenna reflectors).