Modelling, design & thermochemical analysis of a 10 N monopropellant High Test Peroxide-HTP-thruster for space applications

As a green propellant, the researchers shows an increasing interest recently in using High Test Peroxide (HTP) for low cost attitude control systems. It is considered actually as the alternative propellant because it is environmentally friendly, non-toxic, ITAR-free, low cost, and easier to store and handle than the traditional hydrazine-based fuel, also it gives a significant fee saving associated with the test facilities. The present study covers the modelling and design of an HTP monopropellant thruster for ground testing with nominal rating of 10 N sea level. Design, mathematical model, and specifications are presented, followed by the results of the study, which was conducted to define the key dimensions needed (Exit area, Throat area and catalyst dimensions). The main details about the specific concepts of the thruster and the choice of components are provided; with concern for instrumentation items to be used during the next phase which is the experimental validation.