Description
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 N2O 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.
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Details
Title
- Small-scale hybrid rocket test stand & characterization of swirl injectors
Contributors
- Summers, Matt H (Author)
- Lee, Taewoo (Thesis advisor)
- Chen, Kangping (Committee member)
- Wells, Valana (Committee member)
- Arizona State University (Publisher)
Date Created
The date the item was original created (prior to any relationship with the ASU Digital Repositories.)
2013
Subjects
Resource Type
Collections this item is in
Note
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thesisPartial requirement for: M.S., Arizona State University, 2013
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bibliographyIncludes bibliographical references (p. 85-86)
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Field of study: Aerospace engineering
Citation and reuse
Statement of Responsibility
by Matt H. Summers