The comparison of operation and sensitivity of effective parameters in hydrogen peroxide and nitrous oxide thrusters using uncertainty analysis

Nowadays importance of thrusters in movement of space bodies is not obscure. This article is devoted to study and compare two 5 newton lab-scale thrusters Hydrogen peroxide and Nitrous oxide using uncertainty analysis in order to select the more exact and desirable one in case of produced thrust. The data are extracted from experiments tested in aerospace research-center lab. Hydrogen peroxide thruster specifications are 85% of sincerity, 0.15 bar pressure drop in injector, 150 units of catalyst activity, 0.05 bar ambient pressure and 0.01 amount of feed load. On the other hand specifications of Nitrous oxide thruster are 7.36 gr/s mass flow rate, 2.017 mm diameter of throat. Based on calculations, total uncertainty and relative uncertainty for hydrogen peroxide thruster obtained respectively 0.53, 0.73(or14.68%). These amounts for nitrous oxide thruster obtained respectively 0.52, 0.53(or10.27%). Finally the results show that application of nitrous oxide thruster in terms of accuracy, is more desirable and the amount of it’s produced thrust is closer to the amount of five newton desirable thrust.