In space missions, in which materials can be scarce, CO2 appears as a valuable resource t

Background and justification: ​

• Xenon storage is challenging for small satellite platforms due to the strict thermal management and the presence of high-presure components.​
• A way of solving this problem is by having a different storage method. By storing the xenon in a cool gas generator, the xenon is bound chemically before the activation of the xenon cool gas generator. This way there is no need for high pressure components and the strict thermal management of the whole system is no longer needed​

Achievements and status: ​

The SpaceLiner Main Engine (SLME) designed by SoftInWay Switzerland and DLR-SART funded by GSTP with European Space Agency (ESA) is a 200t class staged combustion engine designed for reusable heavy launch applications. The SLME-NIOPP features an Integrated Oxygen Power Pack (NIOPP) in-line with the Main Combustion Chamber. The SLME-NIOPP architecture is unique for Europe and offers significant advantages for Thrust to Weight Ratios. The relatively low combustion chambers and turbine inlet temperatures result in a cheaper and more accessible engine.

The need for high-thrust propulsion systems compatible with small satellites for constellation deployment, orbit maintenance and stationkeeping is particularly emerging. A high-thrust propulsion system provides large velocity increments in a short time, which enables orbit transfer, orbital plane change, re-entry, and planetary orbit insertion for deep space exploration.

System modelling tools allow analysis of the propellant chemical and fluid dynamic behaviour through the complete propulsion system, from the tanks through the connecting pipes, valves, manifolds, combustion elements and nozzles. These tools support the design and verification of rocket propulsion systems and troubleshoot anomalies during the utilisation phase.The appearance of new propulsion concepts necessitates extensions of these numerical tools.

A clustered rocket engine is made up of smaller, easier to manufacture thrusters that can be controlled individually instead of a single, more expensive combustion chamber: thrust vector control (TVC) can be achieved via differential throttling, reducing the need for heavy gimbals and actuators.The proposed activity targets the development of TVC methodologies that are able to effectively cope with independent throttling capability as well as handle failures in one of the cluster?s engines.

North-South station keeping, orbit raising, deep space missions and formation flying of two or more spacecrafts are domain of electric propulsion (EP). Development of neutralizing element - a necessary thruster system compaonent- with high life time, low power consumption and high reliability is the same challenge like the thruster development itself.Having a neutralizing element is mandatory. During ion thruster operation, poisitve ions are extracted from plasma on different principles dependant on the thruster type.