![]() ![]() Several reactant mixtures were utilized in the study to determine the relative importance of different oxidizing species (such as H2O, OH, and CO2). The RMS is a gas rocket with the ability to vary the combustion-product species composition by systematically varying the flow rates of gaseous reactants. The second test rig is a non-metallized solid- propellant rocket motor simulator (RMS). The first is an instrumented solidpropellant motor (ISPM), which uses two baseline solid propellants one is a non-metallized propellant called Propellant S and the other is a metallized propellant called Propellant M. The objective of this work was the study the nozzle erosion rates at a broad range of pressures from 7 to 34.5 MPa (1,000 to 5,000 psia) using two different rocket motors. However, erosion of the nozzle throat region, which is a strong function of operating pressure, must be controlled to realize the performance gains of higher operating pressures. Understanding of the processes that cause nozzle throat erosion and developing methods for mitigation of erosion rate can allow higher operating pressures for advanced rocket motors. ![]() Nozzle erosion characterization and minimization for high-pressure rocket motor applications ![]()
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