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.

This proposal addresses sub-topic 1: R&I on new scalable satellite platform concepts and building blocks increasing the degree of satellite modularisation. SCHUMANN ambitions to strengthen the foundations of the future space ecosystem, by means of 2 complementary developments: (1) a Functional Spacecraft Module (FSM) consisting of a Refuelable Tank (RTa), along with a refueling experiment setup to support the testing and qualification of this module. This FSM will demonstrate that a “side”, standalone module development, by following appropriate design rules and leveraging previous OG developments, can be integrated at a late stage into an IOD mission. (2) a “Design and Development Specification for the Spacecraft Construction Kit” (DSSCK) consisting of a specification and tools aimed at guiding and supporting FSM developers, to make their modules compatible and usable in a single ecosystem.

Orbital modular robotic is a key factor to support sustainability in Space. It is then possible to combine modular components to either create a satellite or, in the event of malfunction, to replace a module. To connect such modules, standard interconnects with multifunctional features are required. The standards provide the laws to connect the space along different functional lines including among those mechanical, electrical, thermal, data and fluidic. For the On-Orbit Servicing market, these standards play a key role to enable space connectors to mate two spacecrafts in a universal and serial way. Several European solutions are already available with a reasonable level of maturity to mechanically connect two space elements and provide data and power transfer. However, there is not a set of common recommendations agreed on by representative European users of space connectors. Considering the huge impact of these multifunctional interconnects at system level, it seems critical to first foster cooperation among them to enable a higher level of standardization to assemble future elements coming from different sources. The main objective of this project is to pave the way for a more flexible, universal and serial interface (USB-type) leveraging the existing standard interconnects for On-Orbit Servicing and assembly applications. After the definition of a standardization level, the design of a universal and serial standard interface will be proposed and demonstrated orienting its features towards compactness, docking symmetry, large docking misalignment tolerances, large loads transfer, data/power transfer redundancy and especially interoperability with other interfaces. Currently interoperability is the only remaining requirement which is not met by any existing space connector/interface. The project will then perform a dedicated experimental benchmark to confirm the achievement of this specific requirement as well as its prospective industrial exploitation.