Hybrid infrared detector arrays combing a sensitive diode layer bonded to a CMOS readout circuit are baselined for many current and upcoming Earth Observation missions. This activity aims to develop a breadboard, using a custom ASIC, capable of providing the necessary clocks and bias voltages to operate the detector as well as providing 4-channel video processing and digitisation, leading to a two-chip (Control ASIC + hyrbid detector) detection system. The design will be split to allow separate or combined use of bias and clock generation and video processing and digitization functions.

The definition of the On-board Software Reference Architecture (OSRA) has led to the definition of a main model (the architecture itself, defined in OSRA), supported by other models focusing on specific aspects such as real-time, transaction, bus exchange, etc. or making the link with system such as the Spacecraft Data Base. The space system primes and space software providers have been starting to use various modelling languages (UML or DSLs) and various tools to support their in-house tailored software engineering processes.

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.

The activity aims to develop techniques (e.g. high sensitivity algorithms, data wipe off for Galileo, optimal data plus pilot combinations etc.) in order to enhance the capability of mass market receivers taking into account their typical resources constraints (limited power, memory, open loop platform etc...). The activity shall investigate the application of these techniques for phase and code tracking down to the detailed design of the techniques for different type of usage and in different type of environment.

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Increasingly demanding space-based applications require a large primary mirror diameter, on which the optical instrument resolution depends. However, the mass and volume of a monolithic primary mirror would dramatically increase along with its size, which, in addition to cost and technical issues, is also limited by the available volumen in the launch vehicle fairing.

This study aimed to demonstrate the feasibility, use and functionality of carbon fibre-reinforced flexible epoxy (CFRFE) materials for self-deployable space structures (such as deployable tape-spring hinges) by designing, simulating, manufacturing, testing and correlating a classic (100% carbon fibre-reinforced plastic -rigid resin- CFRP) deployable tape-spring hinge and a CFRFE deployable tape-spring hinge and compare their mechanical and dynamic behaviours.