Space Based Solar Power concepts promise the generation of large amounts of renewable power by launching vast Solar Power Satellites (SPS) into space and beaming the power back to rectennas on Earth. Due to diffraction physics, large scale arrays delivering 2GW of power to the ground will be on the order of a kilometre in length and have masses between 2,000 and 10,000 tonnes. As of January 2020, the amount of debris orbiting the Earth exceeded 8,000 metric tonnes. A decommissioned SPS would therefore have the potential to create a step change in the mass of debris humanity has created.

Solid state optical refrigeration is the only active cryocooling technique that is truly vribration free, due to absence of moving parts and mass transport, with significant potential for use in future space missions. However, the overall wallplug efficiency is still relatively low in current approaches. One alternative approach investigated here is using a solar pumped laser (SPL) to drive the optical cryocooling process. This approach could offer higher efficiency by eliminates two conversion losses.

In terrestrial electronics, a number of technological solutions have been developed and verified to allow direct (power) SMD EEE components mounting on PCBs with very good thermal conduction properties to the applicable thermal sink/baseplate.There are different principles (from rather basic - Insulated Thermal Substrates to Filled Thermal Vias, combination of Microvias and Buried Vias - to advanced approaches - including micro heat pipes embedded in PCBs).See for example the information provided at the following web links:a.

The E.Inspector mission objectives are to:* Image an ESA owned space debris in its current status * Use obtained images for the verification and validation of the e.deorbit or space tug GNC sensorsFollowing a successful ESA internal CDF study, the mission is now proposed to go to phase A to be studied by industry.Several drivers make this mission design challenging:* A possible long and large (delta-V) transfer to the target* Compliance to Space Debris Mitigation guidelines from possibly high altitude* A close RDV while maintaining keep-out zones and ensuring passively safe trajectories* Tr

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During this activity, we were able to evaluate our electrochemical system with respect to: (i) silicon anode fabricated at an industrial scale equipment, (ii) pouch cells that were manufactured at different suppliers and tested by Airbus Defence and Space, and (iii) safety protocols.

In addition, we showed that standard graphitic-based chemistry cannot operate at low temperatures. Finally, we evaluated the Cost of Ownership of our products.