• Developed Boost MPI parallelized tool development for simulation of space traffic management in anticipation of highly congested space environment policy decisions, including leading the build-out of conjunction assessment, high Pc remediation optimization, and complex station-keeping strategies, parallelized with Boost MPI.Led team to design and deploy tool for cascading collision assessment of active satellites to forecast viability of generic maneuvers against arbitrarily large catalogs beyond single known conjunctions.• Conducted trade studies for satellite formation design on a variety of ground station tracking and geolocation tasks, delivering recommendations for high-level CONOPS to government customers.• Implemented 6 DOF capabilities and multiple complex maneuver strategies (differential drag, RPO station keeping), in a high fidelity satellite propagation C++ library to support customer needs.• Architected JSON interface and implementation through RESTful API to submit a wide variety of propagation tasks to multiple containerized propagation services, streamlining end-user experience.• Led development of Python library to convert propagation tasks from one tool to another, including multiple Aerospace and NASA tools, and compare propagated trajectory outputs.• Developed Unscented Kalman Filter in Fortran to study covariance evolution in cislunar orbital regimes, informing COLA remediation, disposal trajectories, and shared covariance database update cadence.• Improved method to convert CRTBP to multi-central body high fidelity ephemeris model, enabling transformation from initial guesses to realistic periodic orbits with multi-shot optimization.• Built python tool to pull and process daily high-fidelity WAM-IPE weather data in NET-CDF4 format for operational drag/re-entry analyses.• Verification and validation of third-party ephemeris propagation and orbit determination software against trusted Aerospace tools

• Thermal/ fluid analysis on variety of cryogenic liquid rocket engine components, with a focus on regenerative cooling channels. • Developed quasi-1D fluid flow model for rapid regenerative cooling channel rectangular geometry design studies, validated with Thermal Desktop models. • Performed analysis on design geometry regenerative cooling channels in Thermal Desktop, validated with test data. • Optimization of regenerative channel geometry design in Thermal Desktop for thermal performance and structural support. • Developed rocket engine heat flux estimation based on Bartz correlation in MATLAB. • CFD on early-stage and late-stage design cycle cryogenic pumps, turbines, and flow control valves. • Designed joints and flanges between main thrust chamber assemblies and nozzle extensions to reduce thermal stress for structural compliance. • Compartment purge/ venting analysis on SLS USA rocket compartment in Thermal Desktop and CFD, validated venting designs with test data.

• Development of milli-Newton level propulsion system for cubesats designed to hop along the surface of small asteroids to work as a system of systems, able to actuate hopping and 2 axis attitude control during flight. • Analysis and creation of quasi-2D flow model for conicval micro nozzles, fabricated with microfabrication techniques, for rapid prototyping of designs and optimzed with a self-written particle swarm optimizer. Investigated candidate optimal solutions in ANSYs FLUENT CFD. • Designed micro-valves to actuate propulsion system with microfabrication techniques, based on a variety of piezoelctric actuation techniques. • Devloped control laws for hopping along the surface of an asteroid with single-shot Lambert solver with polyhedral shape models of asteroids and relevant self-derived perturbations. Analyzed propulsion system’s capability an attitude controller with a self-design variable sliding mode controller, which won a place in the student competition at the 2019 AAS GNC conference. • Chief engineer on 1U asteroid surface hopping robot, leading a team of undergraduates to raise TRL of the system. • Characterization of electric solid propellants, including calorimetry and thermal gravimetry. • Designed milli-Newton level thruster test stand to validate propulsion system analysis. • Developed control law for optimal control of a solar sail for a Voyager-like trajectory to escape the solar system as a graduate project. • Estimated propulsive requirements for other grad-students’ projects for such purposes as de-orbiting lifetime requirements, interplanetary transfer trajectories, and RPO.

I have worked as a TA and grader for various undergraduate and graduate engineering courses. I have graded for courses in dynamics, thermodynamics, engineering component design, and advanced engineering analysis. I have been a TA for thermodynamics and dynamics of machines, with responsibilities including creating and grading quizzes between exams and holding office hours to assist students in understanding fundamental concepts and homework problems.

My senior design team was tasked with building upon work previous teams had completed for a dynamically scaled X-56 flying wing aircraft for graduate students to conduct research on. Our main accomplishment was in the design and successful flight of three sets of varying flexibility swept wings to be mounted to a modular fuselage while implementing pressure taps and spanwise IMUs for data collection in flight. As the structures lead, I began by designing the wing spars that run the length of the wing that provides the majority of the wing’s stiffness in SolidWorks and ANSYS. I moved to developing a model of the fiberglass skin in SolidWorks to get an estimate of the actual deflection of each wing with varying stiffness, and the models matched real-world performance within 15% for all test cases. I designed the composite layup schedule and oversaw the manufacturing of the molds and wings. I then experimentally determined the eigenfrequency and vibration dynamics of the wings to constrain our desired flight envelope, mainly to avoid flutter.

I was tasked with recreating the results from a previously reported conference paper on a cis-lunar flyby for a low thrust cube sat mission in GMAT. The cube sat was launched on an Earth escape trajectory, with a burn before lunar flyby such that the cubesat passes around the Earth-Sun L1 point. Another burn is initiated to send the cubesat back to the Moon. Lastly, Lunar distant retrograde orbit is obtained and burns spiral the cube sat to a lower altitude. Three control nodes are utilized: at the flyby burn, L1 burn, and Lunar DRO burn.

In Formula SAE, we design and compete a formula style race car against many other collegiate design teams. As body sub-team lead, I managed the design and manufacturing of a lightweight carbon fiber body.

Developed pointing system for high altitude balloon borne telescope. Assistance in integration systems for proprietary balloon technology. Preliminary research for balloon-borne azimuth pointer.

Built hobby rocketIntroductory RC airplane construction and flight

During my senior year of high school, I competed in the Real World Design Challenge - Aviation national competition.

As the President of my school's chapter of the Future Business Leaders of America, I coordinate chapter events alongside the other chapter officers. This includes community service, fundraising, and social events. I try to make FBLA the best experience possible for the other members, so that the organization may be as beneficial to them as it has to me.

As the Vice President of Public Relations, I create and submit press releases to the other State Officers of FBLA Arizona, and I create and submit press release templates to local chapters of FBLA at high schools, so that they, too, may advertise FBLA. I also seek media coverage for FBLA events and conferences, and work with the Vice President of Media Relations to "capture" other member's stories.