SYSTEM ARCHITECTURE AND ASSEMBLY TECHNOLOGY PLANS

Kurzfassung

Systems Architecture NEO deflection and lunar bases are potentially the main business cases as discussed on the System Architecture and Assembly Session on the MEGAHIT workshop in Brussels. Utilisation of existing ISS modules and services should be investigated in-depth, since it can potentially reduce the cost e.g. regarding technology demonstration of robotic assembly and disintegration of S/C modules. For long term (in the years 2040-2050), a parking station in space, which can be used for e.g. replacement of propellant tanks, subsystem or payload modules (mother ship concept in space) can increase the efficiency of several missions in MW class. All modules e.g. propellant tanks, service modules, payload modules can be launched independently and deposited on the mother-ship spacecraft. The replacement of modules on dedicated mission spacecraft can take place on demand. The same mother-ship spacecraft can be used for remanufacturing of components, systems in space by using e.g. 3D printing technologies. Latter is not an option for short term vision, however, such kind of options should be considered in early design phases to increase flexibility and reduce cost in the future. Based on the Global Exploration Roadmap (GER) efforts to promote future interoperability of space systems are important. Pursuing interoperability initiatives, such as international standards and common interfaces e.g. International Berthing and Docking Mechanism (IBDM; ESA), will ensure different systems and nations can work together in exploring the solar system. This is a proven approach to lowering the cost and risk of complex missions (Ref: The Global Exploration Roadmap August 2013). For the MW-class Spacecraft e.g. a suitable fluid interfaces, which meet the requirements regarding e.g. high mass flow rate (MFR), high temperatures as needed for high power nuclear spacecraft will allow more flexibility. Large parts of the spacecraft e.g. thermal subsystem can be designed as autonomous systems, which can be launched separately and be assembled in orbit. Currently used fluid I/Fs on ISS/ATV are able to manage only low mass flow rates (MFR). However, the fluid interface (I/F) of the thermal subsystem has a large impact on spacecraft design.