Terrestrial demands on space missions are increasing rapidly in terms of complexity, technology and velocity. Next to navigation (GPS, GALILEO), science (investigation of space and the universe) and exploration (ISS, Mars), two types of space missions are very important for Europe: Earth Observation (EO, for the sustainability of nature and mankind) and Telecommunication (TC, for business and global connectivity). Each mission requires partly unique technologies, which are produced by only very few global suppliers. If these technologies are not available from within Europe, there is a danger that non-dependent missions may not be performed, created and tailored with a consequent loss of sovereignty in political decisions and a loss of market shares. One of these so-called “Critical Technologies” is the “Large Deployable Reflector (LDR)”. Packed in stowed configurations, these reflectors can be accommodated on satellites, which then still comply with the limited launcher fairing volumes. By enlarging the size of the reflector it is possible to offer higher sensitivity and resolution, e.g. for radar missions (EO & science) and implement stronger communication links for e.g. higher data throughput (TC). Within the upcoming eight years the demand for such reflectors will increase worldwide, whereas the Consortium targets a certain market share with its “Large European Antenna (LEA)”. The proposed H2020 project would now enable the combination of the technologies previously developed by the consortium members and the joining of further European entities to fill the remaining gaps and form one strong and complete European team. Through obtaining an EC-grant for LEA, each building block will be upgraded with innovation, adapted to a scenario and qualified to meet one common target, namely: 1st European PFM (including reflector and arm) reaching TRL 8 to be ready for integration by the end of 2020 and for flight in 2021.

There is an increasing demand for advanced materials with temperature capability in highly corrosive environments for aerospace. Rocket nozzles of solid/hybrid rocket motors must survive harsh thermochemical and mechanical environments produced by high performance solid propellants (2700-3500°C). Thermal protection systems (TPS) for space vehicles flying at Mach 7 must withstand projected service temperatures up to 2500°C associated to convective heat fluxes up to 15 MWm-2 and intense mechanical vibrations at launch and re-entry into Earth’s atmosphere. The combination of extremely hot temperatures, chemically aggressive environments and rapid heating/cooling is beyond the capabilities of current materials. Main purpose of C3HARME is to design, develop, manufacture, test and validate a new class of out-performing, reliable, cost-effective and scalable Ultra High Temperature Ceramic Matrix Composites (UHTCMCs) based on C or SiC fibres/preforms enriched with ultra-high temperature ceramics (UHTCs) capable of in-situ repairing damage induced during operation in severe aerospace environments. C3HARME will apply to two main applications: near-ZERO erosion rocket nozzles that must maintain dimensional stability during firing in combustion chambers, and near-ZERO ablation thermal protection systems enabling hypersonic space vehicles to maintain flight performance. C3HARME represents a well-balanced mix of innovative and consolidated technologies, mitigating the level of risk intrinsic in top-notch research and innovation development. C3HARME starts from TRL of 3-4 and focuses on TRL 6 thanks to a strong industrial partnership, including SMEs and large companies. To reach TRL 6, rocket nozzles and TPS tiles with realistic dimensions and shape will be fabricated, assembled into a suitable system, and validated in a relevant ambient (environment centered test). Project results could be easily extended to the energy, medical and/or nuclear environments.