• Executed ten Hotfire tests for Raptor for a combined duration of 1000 seconds (ATP & DEV Tests)• Acted as test conductor on Raptor Vertical Stand for flight-critical Raptor B9 development testing to build vehicle flight rationale for OFT-2• Performed sub-cooled cryogenic propellant operations, pre & post test checkouts for Raptor, and daily operations unique to SpaceX• Developed & integrated software that estimated propellant consumption for each Hotfire attempt across Raptor Site• Implemented new operational procedures across Raptor Vertical Stand that contributed to more efficient Hotfire test recycling & increased stand safety readiness

• Executed four Hotfire tests for BE-3U & BE-3PM for a combined duration of 400 seconds (ATP & DEV Tests)• Acted as test conductor on GEEx test stand for early BE-3U development & post New Shepard anomaly BE-3PM testing• Performed cryogenic propellant transfer operations, daily stand checkouts, and assisted with post-test stand data review• Sized & implemented sharp edged-orifices that decreased test stand complexity & redundancy by replacing upstream throttle valves• Designed & helped fabricate a 3K PSI Helium Panel that improved efficiency in daily operations, increased pressure visibility for technicians, and enabled greater venting capabilities for increased LOTO capacity• Improved pressure visibility & increased safety capabilities across test stand by integrating pressure transducers in new locations

• Led the post-processing of our flight engine’s regeneratively cooled, additively manufactured GRCop-42 combustion chamber• Helped create GD&T of our combustion chamber for post-processing machining and made the executive decision of using machinable wax in our lower manifold• Created a cost-free, scrappy test stand that enabled us to water-flow our combustion chamber and run a mixture of chemicals through our regen channels to remove the oxidation layer created by HIP to ensure steady heat transfer• Assisted in making modifications/upgrades to our test stand for injector cold flow and potential engine hotfire

• Directed a group of 8 Individuals on the Propulsion Team at Texas Rocket Engineering Lab

• Working with fellow student engineers to design, build, and launch a 30-foot rocket (Halcyon) 100 kilometers up to the Karman line• Helped develop our flight 3,500 Ibf liquid bipropellant rocket engine (TXE-2 Havoc)