New applications for ESA Future Launchers Programme

In the general catalytic igniter concept a catalyst is applied to decompose a propellant, thereby releasing thermal energy. In our current design hydrogen peroxide is decomposed into a high temperature mixture of water vapour and oxygen. This can in turn be used to ignite a mixture of propellants in a thrust chamber. The advantage of the catalytic concept is that no regulated electrical device is needed to ignite the propellants in the igniter. Compared to a spark torch igniter, the ignition electronics and the spark plug can be omitted. The Direct Spark Ignition principle is based on creating plasma directly in the engine’s combustion chamber at a location favourable for ignition, similar to a gas-turbine engine. If successful, this system would make the use of a traditional torch igniter and feed-system obsolete with potentially massive savings in mass and costs.