Fuel Regression Rate Characterization Using a Laboratory Scale Nitrous Oxide Hybrid Propulsion System

Abstract

The purpose of this study was to characterize the regression rates of three traditional hybrid rocket fuels along with one novel fuel using nitrous oxide as the oxidizer. In order to complete these tests, a robust test facility was developed for use in this study as well as in future hybrid rocket programs at Stanford University. This stand allowed for rapid successive hot fire testing and the capability to test multiple fuel grain configurations. To date it has been used to conduct 40 hot fire tests. Performance values and fuel regression rate data are presented for HTPB, PMMA, HDPE, and sorbitol.