Design and development of 10N solid rocket thruster

The present study proposes to design, fabricate and test the solid rocket thruster using the KNSU propellant consisting of Potassium Nitrate as the Oxidizer and Sucrose as the fuel. Basic grain geometry like an internal burning tube is chosen to simplify the analysis. This study consists of the Combustion chamber and Nozzle design. Hereby, the thickness and geometry of the chamber is based on the maximum pressure and quantity of the propellant respectively. Nozzle design is based on the pressure ratio of 30 between the chamber and exit. The design of the nozzle is further verified using the Ansys Fluent software. With the above geometry of propellant and nozzle design, the thrust calculated will be around 10N. Fabrication is done using the stainless steel as the material due its properties of availability and higher melting points. The results obtained in the experimental phase are compared with theoretical calculations.