Effects of Swirl Injector Design on Hybrid Rocket Fuel Regression Rate

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Presentation transcript:

Effects of Swirl Injector Design on Hybrid Rocket Fuel Regression Rate Testing and Results Effects of Swirl Injector Design on Hybrid Rocket Fuel Regression Rate Presented by Kyle Bowerman Team Member, Raul Lugo Mentor, Matthew Summers

Presentation Summary Motor Design Test Setup Results Conclusion Future Endeavors Questions

Motor Design Simplistic Design Rapid Integration of Components Use of Forward and Rear Enclosures Easy to Change Injector and Grains

Test Setup Importance of Safety and Reliability Nitrous Oxide Tank and Line Integration of Three Pressure Transducers and Two Load Cells Venturi Meter Sytem Thrust Mass Flow Rate of NOS Pyrodex Pellet-Bridgewire Igniter DATAQ DI-718B Data Acquisition System

Test Video 60 Degree Injector

60 Degree Swirl Injector Results Average Burn Time: 5.12 seconds Initial Spike Due to Solid Igniter Propellant Average Thrust of 36.63lbf Average Chamber Pressure of 114.2 psi

60 Degree Swirl Injector Results Mass Flow Rate of 0.2370 lb/s Results for Thrust, Pressure, and Flow Rate Were Lower Than Expected Due to the Oxidizer Tank Nearing Empty After Many Cold-Fire Tests Regression Rate of Grain Was Calculated to be 0.0314 in/s

Grain Post and Prior Burn

Conclusion & Future Work The Preliminary Tests on the 60 Degree Injectors Aided in the Understanding and Experience of Conducing Hot Fire Tests Future Tests Will be Carried Out on Each of the Swirl Injector Designs to Properly Characterize Each Injectors Effect Oxidizer Mass Flow Rate, Burn Time, and Ignition Events Will be Regulated for Future Tests to Ensure an Improvement of the Accuracy of Data Obtained Grains Will Undergo Molding From a Foam Based Material to Help Measure the Difference Grain Volume Prior and Post Burn

Special Thanks ASU NASA Space Grant Consortium Raytheon Company Matthew Summers

Thank You! Questions & Comments