Owned the subsystem designs for woody biomass handling for a 10X scaled pyrolyzer• Designed a biomass handling subsystem from clean sheet, conducted concept and detailed design reviews, released a complete drawing package, solicited quotes from contract manufacturers, and purchased the subsystem• Enabled biomass handling throughput to increase by 10X while reducing operator loadSupported the design and testing of a woody biomass injection system for a 10X scaled reactor• Supported biomass injection design from clean sheet, reviewed drawing package, wrote a test plan, and conducted subsystem testing to verify performance after receiving hardware• Proved biomass injection strategy for the 10X scaled reactorOwned the design and build of a pyrolyzer test system focused on reactor operation• Owned support equipment design: biomass handling and injection, post-reactor process stream handling, and byproduct offtake• Designed equipment from clean sheet, performed structural analysis, conducted design reviews, released drawings, coordinated fabrication, electrical, and software work, drove the assembly process, and conducted initial system tests• Enabled the Charm test team to operate a reactor focused system to accelerate pyrolysis learningsOwned the design, build, and testing of a new corn stover biomass test system• Owned all aspects of mechanical design, conducted design reviews, released drawings, coordinated fabrication, electrical, and software work, drove the assembly process, and completed a test campaign• Proved system capability for consistent higher throughput and accurate metering of materialCreated 3D CFD simulations to vet alternate reactor geometries in support of a reactor design reviewPerformed tests on various components and subsystems to inform design changes and fixes to existing pyrolizers• Oxygen sensors, rotary valves, butterfly valves, etc.

Owned 1D fluid system models of Launcher One’s first and second stage cryogenic helium propellant pressurization systems• Developed flight data driven correlations to predict helium states between on-orbit engine burns of stage 2• Conducted worst case analyses to close systems requirements for each flight• Defined system requirements for next block upgrade of Launcher One with a redesigned second stage• Owned model of first and second stage propellant tank flight pressure profiles• Built a model in MATLAB to determine required propellant tank ullage pressures in order to satisfy turbopump inlet pressure requirementsDeveloped 1D CFD model to predict bounding thrusts of oxygen vents on stage 2 to help mitigate control authority issues in spaceConducted vibration testing of stage one solid propellant settling thrusters• Designed vibration testing mounting hardware• Rapidly modified and qualified final designCoordinated across three teams to complete propellant settling verification CFD for each flight of Launcher One

I interned with the Stage Systems group within Propulsion at Virgin Orbit. My main project was a thermofluid analysis of the propellent and pressurant management system of Launcher One's second stage.- Create models in MATLAB to estimate bang bang valve behavior and fluid properties within the stage 2 tanks- Created simplified geometries of fuel and liquid oxygen lines in NX- Linked those models to Thermal Desktop using Spaceclaim- Used Thermal Desktop to run SINDA/FLUINT to determine the pressure profile of stage 2 at various points throughout flight. This was an iterative process involving anchoring to stage test data and interfacing with turbopump and engine teams to ensure the second stage operates within the required pressures and temperatures. Other projects included:- Fault tolerance studies for removal of valves on stage 2- Procedures for final rocket inspection and rocket leak checks

Interned with the Components group within Propulsion at Virgin Orbit. Focused mainly on development and qualification testing of valves and regulators and designing test hardware. Main projects included:- Development testing of two pressure regulators that appear on stage 1 and stage 2 of Launcher One- Qualification testing of an in-house designed pneumatically actuated cryogenic valve with active and passive relief capabilities- Design of vibe bracketry for a variety of components, from a fuel trim valve to check valves, using NX to create models and engineering drawings- Dissasembly and inspection of a turbopump used on a Newton 4 hotfire- Development of leak check procedures for stage 2 integrated testing

I earned a grant from the engineering school at Princeton University to design and build two high power rockets and pursue certification from the National Association of Rocketry. The first rocket is capable of reaching an altitude of 2,250 feet and has a delay charge powered parachute deployment. The second rocket is a fiberglass minimum diameter rocket capable of reaching 10,000 feet and going supersonic. This rocket has an electronically powered altimeter for triggering dual deployment recovery. I personally did the layups of the fiberglass airframe and fins. Both rockets will be flight tested this fall.

Worked as a member of Princeton Rocketry Club's CanSat team in charge of designing a compact circuit board to power the electronics within a small glider to be deployed at 2000 ft. Used PTC Creo and KiCad to create the component layout and circuit board design. Interfaced with Osh Park to manufacture the curcuit board and built it into the glider.