● Perform high level trade studies to drive component placement and selection on Haven-1● Lead radiator design and development on Haven-1

● Responsible for designing TPS from nose to tail on LauncherOne rocket using Thermal Desktop (65+ models)● Developed end-to-end aerothermal database from CAD cleanup to aeroheating profiles encompassing flight envelope● Drive innovation in current workflows and processes to decrease production time by 10s of hours per rocket● Perform aerothermal analysis of NewtonThree rocket engine TPS● Interface with manufacturing teams to support TPS production and integration on LauncherOne vehicle● Provide real-time engineering support during critical operations (such as launch and wet-dress rehearsal)

• Lead overall CAD mechanical and thermal design in SolidWorks• Interface between different engineering subteams• Manage risks and requirements to ensure overall mission success• Responsible for modeling and simulation of experiment which is designed to study radiative coating efficiency on the lunar surface• Design material coatings and sensor layout in order to optimize ∆T across the sensing face using SolidWorks Simulation and optimization tools• Reduced weight by 35% by use of light-weighting techniques during the design phase• Minimized power usage with SolidWorks optimization tools while still meeting scientific objectives• Simulate thermal conditions using Thermal Desktop across lunar day and night including effects due to proximity to lander and lunar surface• Validate thermal-vacuum chamber sensor experiments at NASA Johnson Space Center using SolidWorks simulations• Provide feedback to JSC team about performance of sensor• Assist with thermal-vacuum testing of hardware to validate simulation results

• Responsible for determining relevant flow physics responsible for transitional heating and drag increases• Harness Pointwise gridding software to generate 2D and 3D hexahedral watertight meshes for use in our CFD solvers• Automate meshing process using TCL-based script in Pointwise to decrease meshing time from days to minutes• Generate high resolution (>100 million cells), high resolution laminar basic states using DPLR, US3D, and OVERFLOW CFD codes on complex hypersonic geometries• Visualize and analyze solutions using Tecplot 360 and Matlab• Work with experimentalists to interpret wind-tunnel and flight results using CFD• Compare with experiments to match quantities such as heat flux data and disturbance measurements• Collaborate with hypersonic wind tunnels to inform sensor placement and model design based on CFD simulation results• Employ in-house data extraction code to extract paths from various basic state solutions.• Analyze boundary-layer disturbance growth rates using Fortran stability code EPIC• Characterize primary instabilities such as 2nd mode, stationary crossflow, and traveling crossflow using both linear and nonlinear parabolized stability equations stability techniques

• Responsible for devising AggieSat6 satellite software architecture to maximize reliability in space• Lead and mentored younger team members on the topic of in-space design• Interfaced with guidance, navigation, and control (GNC) subteam to communicate pointing requirements across other subteams• Managed and worked to understand risks from GNC subsystem to determine overall impact on AggieSat6• Formulated requirements verification matrix to ensure that AggieSat6 meets all mission objectives

• Worked as a vehicle analysis intern with the aerothermal group at SpaceX• Expanded flow solver capability in order to decrease time to solution• Performed aerothermal computations on the Crew Dragon capsule at hypersonic reentry conditions in order to investigate heating on the vehicle• Developed a tutorial that served to demonstrate how automation in the meshing process prior to CFD can be used to save time during an analysis• Supported hypersonic aerothermal flow analysis on the Starship vehicle by performing CFD simulations.

• Responsible for CFD analysis of rocket and managed rocket assembly in Solidworks with 100+ individual parts• Designed 3D printed nose cone and structural bulkhead to withstand 500 lbs. of force from parachute• Hand-fabricated 24 fiberglass composite body tubes, engine casings/liners, and fins using wet composite layups techniques• Hand-cast solid rocket fuel grain and sliced up into individual segments prior to integration into motor

• Helped assemble solar panels onto and assisted with vibrational testing of the satellite• Developed flight software that interfaces with the on-board GPS unit and the on-board magnetic field sensor in C++• Worked with these same areas in our simulation of the satellite in Simulink

• Collaborated on development of a C++ library to control the on-board camera on our spacecraft.