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Analytical and Empirical Characterization of Hybrid Rocket Swirl Injection

Analytical and Empirical Characterization of Hybrid Rocket Swirl Injection. Presenters: Matt H. Summers Advisor: James K. Villarreal. Daedalus Astronautics. Dual Purpose: Teaching rocketry and basic physics to k-12 students Advanced propulsion research/Sounding rockets.

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Analytical and Empirical Characterization of Hybrid Rocket Swirl Injection

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  1. Analytical and Empirical Characterization of Hybrid Rocket Swirl Injection Presenters: Matt H. Summers Advisor: James K. Villarreal

  2. Daedalus Astronautics • Dual Purpose: • Teaching rocketry and basic physics to k-12 students • Advanced propulsion research/Sounding rockets Daedalus Astronautics

  3. Project Motivation • Analytics: • Preliminary computational fluid dynamic analysis • rapid results • Low cost • Empirical: • Minimized testing – Low cost • Develop an empirical characterization of hybrid swirl injection • Future Work: • Ability to test multiple components of a Hybrid Rocket Motor • Long-term, low-cost, easy apparatus • Great predictor for future research Daedalus Astronautics

  4. Analytics • Results: • 600 psi Tank Pressure • 400 psi chamber pressure • Turbulent flow achieved • Increased oxidizer mass flux CTRZ: Central Toroidal Recirculation Zone Figures shown are using a 60° super-critical injector. Top-Right: Density distribution in CTRZ flow structure. Bottom-Right: Constant pressure distribution in HRM. Left: Varying Temperature distribution in HRM. Daedalus Astronautics

  5. Design • Selected Injectors: • No Swirl • 0° Swirl • 15° Swirl • 20° Swirl • 30° Swirl • 35° Swirl • 42° Swirl • 60° Swirl Figure here shows how hybrid swirl injectors are classified based on their radial injection angle. Daedalus Astronautics

  6. Fabrication • Selected Injectors: • No Swirl • 0° Swirl • 15° Swirl • 20° Swirl • 30° Swirl • 35° Swirl • 42° Swirl • 60° Swirl Example of print created for the 42° swirl injector Machined injectors with their respective swirl angles Daedalus Astronautics

  7. Cold-Flow Testing No CTRZ present – no pre-heating • Results: • No Swirl Test • 2 sec test • 0.6 lb ∆M in Tank • Mass Flow Rate = 0.3 lb/s • No CTRZ • 60° Swirl Test • 2 sec test • 0.6 lb ∆M in Tank • Mass Flow Rate = 0.3 lb/s • CTRZ Formation Flow of No Swirl Injector Flow of 60° Swirl Injector Forward Enclosure deflects swirl flow to initiate CTRZ Daedalus Astronautics

  8. Hot-Fire Testing Upon completion of the motor case. Before Testing of Full-Scale Hybrid Rocket Motor on Campus After Daedalus Astronautics

  9. Empirical Swirl Flow passing through the Pre-Combustion Chamber Current Equation for regression rate of HTPB fuel grain Potential Equation for regression rate of HTPB fuel grain Daedalus Astronautics

  10. Questions? Daedalus Astronautics

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