The main objective is to develop a standard interface that considers a set of connections that allow coupling of payload to manipulators and payload to other payload. The realization of a modular reconfigurable system depends, among other things, on interfaces, that includes mechanical interfaces connecting the blocks to one other, electrical interface for power transmission, thermal interfaces for heat regulation and interfaces to transmit data throughout the satellite. Multi--‐functional “Intelligent” interface will be considered to interconnect building blocks and also to connect to the satellite with a servicer. The standard interface will require standardization and modularization of the different components in an integrated form (where mechanical, thermal, electrical, data connections are combined) or a separated form. The standard interface shall allow building up large clusters of modules. APMs are considered for demonstration, validation and verification of all properties of the standard interface. An end-effector for a robotic manipulator will be designed according to the layout of the standard interface. The Modular Interface will take into account long duration missions, no logistics support and missions composed of multiple payloads and architectures. Main benefits: - Improve operational capacity - Reduced logistics with common and modular spares - Common maintenance standards - IF architecture flexibility: common infrastructure needed to support the modular design - Mission flexibility (configuration changes) - Standardizes mechanical, data, electrical, thermal Interfaces - Keep existing standards where applicable - Introduce in the design aspects related to interchangeability and interoperability The standard interfaces will allow to develop the SRC end goals. The output of this development will address the Future Low--‐cost EXchangeable/EXpandable/EXtendable SATellite, which targets the demonstration of robotics servicing technology.

The project deals with the replacement of hydrazine within space propulsion systems. It improves significantly the ADN-based propellants currently existing and enables the replacement of hydrazine within the whole operational area of currently used hydrazine propulsion systems. The objectives of the project are: 1.) Replacing hydrazine by adapting the propellant to currently existing materials available in Europe 2.) Development of a cold-start capable ignition system to replace hydrazine in the whole operational area 3.) Verification of the technology within battleship unit(s) to reach a Technology Readiness Level of 5 4.) Adapted numerical models to describe the processes within such propulsion systems. To reach these objectives, the following development will be done within the project A) Propellant development in order to obtain maximal temperatures within the combustion chamber that can be withstand with currently available materials in Europe. Additionally, the propellant will have increased specific impulses in relation to hydrazine. B) Development of catalytic ignition systems to withstand the thermal and mechanical shocks while having cold-start capability C) Design and testing of the corresponding battleship units within the project to verify the achievement of the project experimentally (reach TRL of 5) D) Generating validation results for future purposes to adapt the technology to future purposes. Therefore, the relation to the work programme "Alternative to hydrazine in Europe" is achieved by a replacement of the currently hydrazine based propulsion system with a green propellant system with higher specific impulse.

Independent access to space is a key component of the European Space Policy. The competition is increasing in this area both for the full launching systems and the key subsystems. Cost-effectiveness becomes the main driving factor. HYPROGEO ambition is to study a propulsion module based on Hybrid chemical propulsion. Hybrid propulsion is not a new technology but its application to a transfer module or to a re-ignitable upper stage is very innovative. It is an interesting alternative for the GEO transfer, between the chemical propulsion (bi-liquid) and the new trend of Electrical Propulsion (EP). There are very good synergies and complementarities with the other propulsion activities. The proof of concept (specific impulse, thrust) has been demonstrated. The main technical challenge is the long duration firings. The future development of an operational system, already identified in the current roadmaps, requires advanced R&D work on 4 critical technologies: - Combustion chamber. - High endurance nozzle. - Catalytic injector. - Production, storage and use of high concentration hydrogen peroxide. These R&D activities structure 4 main work packages. A system study ensures the global vision in coherence with an economic analysis, the identification of technical challenges and the consolidation of scientific results. A last work package performs the dissemination of results. An innovative aspect is the fact that the R&D activities are directly driven by the ecvolution of market needs and system requirements. Main expected benefits are: - Green and simpler design (compared to bi-liquid). - Shorter transfer time and reduced cost of operations (compared to EP) A TRL 3-4 level is expected at the end of the project. The impact of the project is secured by the composition of the consortium led by Astrium with the main European actors of the hybrid: it contributes to the consolidation of the European industrial supply chain for Hybrid propulsion. Project duration is 36 months.

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.

We propose the development of a Very High Performance microprocessor System on Chip (SoC) based on STM European 28nm FDSOI technology with multi-core ARM processors for real-time applications, eFPGA for flexibility and key European IPs, enabling faster and cost-efficient development of products for multiple space application domains. The performance is expected to be 20 to 40 times the performance of the existing SoC for space and more than 2 times the performance of the future quad core LEON4 chip. This performance level, combined with a large set of integrated peripherals including dedicated on-chip functions for GNSS, TM and TC support, will enable key space applications to be executed within the same microprocessor significantly reducing cost and mass and boosting competitiveness of future European space equipments. With the highest cumulative number of European satellites and electronics equipments successfully operating in orbit, Airbus and TAS represent together the indisputable best positioned companies in Europe to ensure the maximum relevance of the DAHLIA SoC for its future use by the whole European Space community. Beyond Space applications, the adoption of the ARM processor will enable the convergence with terrestrial applications benefiting from the strong ARM ecosystem while the new SoC will ensure European strategic non dependence for the most critical component on board.