Fluid dynamic analysis and development of a 1 N bipropellant liquid rocket combustion chamber

The New space economy is calling for high performance miniaturized engines for nanosats. Some injection designs for a bipropellant engine have been numerically investigated using RANS CFD methods in order to achieve high combustion efficiency and low convective heat trasfer while being additively manufacturable to reduce costs and the number of parts. Two final designs based on HTP (High-Test Peroxide) as the oxidizer and meeting all these requirements will be presented.