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Served as Chief Mechanical Engineer for development of WashU Satellite’s first satellite, a 10x10x10cm CubeSat designed to provide 3-axis control using an LQR controls algorithm using three club-built magnetorquers
Oversaw design of fully custom 6061 Aluminum frame built to withstand 30G quasistatic loading consistent with Falcon 9 launch requirements
Performed mass estimation using SolidWorks and real-life validation to achieve under 5% error for mass, moments and products of inertia, and center of mass.
Performed vibrational analysis in SolidWorks to determine natural frequency and structural response to launch vibrations
Machined 12 custom corner brackets and 8 custom L-brackets to maximize space and simplify assembly process
Created wire management plan to fit six PCBs, four 18650 batteries, and two magnetorquers in a 10cm form factor
Taught Finite Element Analysis to enable member-performed validation
Assisted with COMSOL thermal analysis integrated with orbital parameters and heat produced from PCBs and custom magnetorquers
Traveled to CalPoly to present on SCALAR at the 2026 CubeSat Developer’s Workshop

THRUST: Garage-built cold-gas RCS thruster | Independent Project | 2023

Designed and built a single-axis reaction control system with two directions of thrust
Machined custom nozzles on a lathe with <0.025in throat diameter
- Determined optimal nozzle geometry using NASA documentation
- Created Fusion 360 model and machining procedures
Safely managed and tested 3000psi system, regulated to 400psi at the nozzles for consistent thrust
- Used a combination of manual valves and blowoff systems to ensure safety
- Performed leak testing with soap bubbles
Wrote C++ control code for Arduino
Designed and soldered an electrical assembly for the control of two 12V solenoid valves
Designed and 3D printed custom nozzle mounts
Demonstrated controlled rotation on a test stand

Enceladus ExoPlume: NASA New Frontiers Mission Proposal | Introduction to Planetary Mission Design | 2025

Chief Mechanical Engineer for a simulated NASA interplanetary mission proposal brought to a CDR level in a class taught by a JPL/NASA employee
Used spreadsheets to calculate:
- Rate budget for data transmission to earth from Enceladus
- Mass budget with a combination of custom components and mass calculations from past missions and proposals, including all scientific instruments
- Power budget for three RTG options and four solar panel options
- Financial budget
Created CONOPS profile for mission’s orbit and coast phases
Built a Risk Matrix and Risk Mitigation Plan for five primary failure modes
Used rocket equation and orbital calculations to calculate dry mass, wet mass, and delta-V budgets for various propulsion options including monopropellant, bipropellant, nuclear, and electric propulsion.
Contributed to a full Science Traceability Matrix for project
Determined Technological Readiness Level (TRL) for all components, and ensured compliance with launch requirements

RACK: Folding modular tow hitch mounting system with bike rack attachment | Independent Project | 2023

Designed and built a foldable fow-hitch attachment with modular attachment points
- Takes up 85% less space than anything I could find on the market when folded
- Successfully held a mountain bike while driving on the road
Modeled a full moving assembly in Fusion 360
Used GD&T as per ASME Y14 with interference and clearance fits
- Achieved successful tolerancing for welded and painted joints
Machined all components
- Used water jet and CAM CNC routing
- Used manual mill
- Welded multiple critical joints

RAILING: Railing set for standard shipping container | Flying Moose Industries | 2023

Programmed repeated, optimized CAM cycles on a CNC Mill to create a set of railings for a standardized shipping container
Used manual mill for roughing passes
Created tooling to optimize manufacturing processes
Welded components together and prepared contact surfaces for welding
Verified manufacturing with calipers
- Achieved successful assembly of all railing sets

Nozzle Optimizer: MATLAB script that optimizes and visualizes cold-gas thruster nozzle parameters | Independent Project | 2026

Programmed a physics‑based fluid‑dynamics optimization tool in MATLAB that calculates optimal thruster input/output angles, exit angles, inlet diameters, expansion ratio, nozzle length, and throat diameter
Matched expected trends and provided optimized values for future thruster project
Programmed a MATLAB visualization to enable intuitive understanding of trends
Identified and modeled accurate assumptions for a simple cold-gas thruster