Derived from the necessity to increase testing capabilities of hybrid rocket motor (HRM) propulsion systems for Daedalus Astronautics at Arizona State University, a small-scale motor and test stand were designed and developed to characterize all components of the system. The motor is designed for simple integration and setup, such that both the forward-end enclosure and end cap can be easily removed for rapid integration of components during testing. Each of the components of the motor is removable allowing for a broad range of testing capabilities. While examining injectors and their potential it is thought ideal to obtain the highest regression rates and overall motor performance possible. The oxidizer and fuel are N 2 O and hydroxyl-terminated polybutadiene (HTPB), respectively, due to previous experience and simplicity. The injector designs, selected for the same reasons, are designed such that they vary only in the swirl angle. This system provides the platform for characterizing the effects of varying said swirl angle on HRM performance.ii DEDICATION I would like to dedicate this work my wife, Sarah Summers, for her continued support and encouragement, especially in those times when she was 9 months pregnant or caring for our new born son, Parker Summers.iii ACKNOWLEDGMENTS I would like to thank James Villarreal, Evan Olson, Chris Karpurk, Gaines Gibson, Ryan Stoner, Richard Stelling, Jacob Dennis, Steven Shark, Brian Franz, and any other person I may have forgot who helped me on this project over the past couple years.
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