Design of a modular one Newton hydrogen peroxide monopropellant thruster, including feed system and test setup
T. Franken (TU Delft - Aerospace Engineering)
Botchu V.S. Botchu – Mentor (TU Delft - Space Systems Egineering)
Ferran Valencia-Bel – Graduation committee member (European Space Agency (ESA))
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Abstract
Hydrogen peroxide has been around as rocket propellant for several decades. It was popular as monopropellant in reaction control thrusters, until the discovery and technical viability of Hydrazine. However, in 2011 the European Commission has added Hydrazine to its candidate list of "substances of very high concern" in its Registration of Evaluation Authorisation and Restriction of Chemicals (REACH) framework, creating an increased interest in the use of "green" propellants, such as hydrogen peroxide, ever since. Traditionally, these thrusters use catalyst beds for the decomposition of high concentrations of hydrogen peroxide. However, several alternative technologies are considered to improve performance. A fully modular 1N thruster has been designed for ground testing and comparison of the performance of different catalyst beds, as well as alternative technologies. It includes the design of a propellant feed system and test setup. To support the design, a mathematical model of hydrogen peroxide decomposition was created.