Los Angeles, California, United States
Citizen of the United States, United Kingdom, and Hong Kong SAR.
• Drive Relativity’s design reliability and criteria effort for the Terran R orbital-class 3D-printed reusable rocket program – act as the focal between the Integrated Performance department and Structures, Fluids, Propulsion, Avionics, and Launch departments for ensuring load, multi-body dynamic, dynamic environment, thermal, aerodynamic, aerothermal, and GNC inputs are met or exceeded for a successful Terran R vehicle design • Serve as the design reliability and criteria engineer for the Terran R thrust structure, tank domes, Aeon R and Aeon R Vac engines, engine valves, engine feedlines, base heat shield and skirt, thermal protection system, landing leg system, grid fin system, thrust vector control system, all fluid systems, and COPVs • Leading company’s revised approach to qualification and acceptance testing for the reusable Terran R launch vehicle, building off the Terran 1 program • Have worked with hardware designers from all Relativity departments in preparing them for successful requirements and design criteria reviews, ensuring analysis inputs, material considerations, and factors are applied to meet or exceeded design needs • Drive decisions on what uncertainty and safety factors the Terran R program uses for how to balance risk and speed
Senior Systems Engineer in Vehicle Development for the Terran 1 rocket • Launch vehicle systems engineer for Terran 1 – the world’s first orbital-class 3D-printed rocket (maiden flight in March, 2023) • Responsible engineer for all Terran 1 Stage 1 hot fire, Stage 2 hot fire, and vehicle static fire test instrumentation – involved determining 300+ sensor channel needs across company departments, purchasing all hardware from vendors, integration of all sensors on vehicle, designing and building harnessing, performing data and control checkouts at test and launch sites, and dispositioning ongoing additions and edits throughout the test campaigns • Created the Terran 1 program’s first Bill of Design tool for summarizing overall vehicle design completeness, risk, and sign-offs for flight readiness • Designed and implemented the Terran 1 program’s first launch day sequence of events and terminal count through a self-designed tool – the integrated sequence directly informed the writing of the stage hot fire and launch state machines
National Aeronautics and Space Administration (NASA) Lyndon B. Johnson Space Center Artemis Program - Lunar Gateway Systems Engineering & Integration Configuration Analysis Modeling and Mass Properties Team Lead • Team lead for the Lunar Gateway space station Configuration Analysis Modeling and Mass Properties (CAMMP) team for the NASA Artemis Program, with the mission of putting the first woman and next man on the Moon by 2024 • Manage the work of a five-person team on the JSC Human Spaceflight Technical Integration contract to support the integrated configuration and performance analyses for Gateway – work directly with Gateway Systems Engineering & Integration management and program office leadership • Lead integration CAD modeler for the Artemis Program’s Lunar Gateway – drew the first solid-body models of the lunar space station for cross-agency analyses and responsible for configuration integration with the Orion Program, Human Landing System, and the European, Japanese, and Canadian space agencies • Oversee numerous configuration and performance trade studies for the evolving integrated stack of the space station including assembly sequence, docking clearance, external and internal configuration layout, Extravehicular Activity (EVA) analyses, solar array shadowing, and Earth and lunar antenna line-of-sight performance International Space Station Systems Engineering & Integration External and Internal Configuration Analyst • ISS internal and external configuration analyst for 11 expeditions to the International Space Station • Determined mass and aerodynamic properties of the ISS for Guidance Navigation and Control’s flight execution after any major ISS change to configuration (installing a payload, docking or undocking a vehicle, robotic hardware movements, etc.) • Performed placement studies for ISS internal volume, determining how the inside of ISS could be configured for new hardware while maintaining all safety ground-rules and constraints
• Verified acceptable vertical orientation operating dynamics of T700 engine adaptation for DARPA/Navy Tactically Exploited Reconnaissance Node (TERN) • Performed aeromechanics analysis to close four Material Review Board (MRB) cases for non-conformed F414 and J85 parts • Determined ideal operation restart times for GE38 engine from Lockheed-Martin Sikorsky CH-53K flight test data to avoid bode rotor start vibration • Lead a sensitivity study to determine acceptable degree of geometry variation in J85 airfoils received from a certain vendor • Quantified stiffnesses and flexibilities of GE38 and T700 impellers using finite element analysis to mature a GE design practice • Wrote the certification report for the 105% power turbine speed enhancement of the YT706 engine
• Supported assembly and test engineers in identifying the root causes of aircraft engine line failures for the GE90, GEnX, and CFM56 engines to decide on the best course of action to recover the engine from a sickbay teardown • Streamlined the assembly and test data acquisition process for the global ATMRO team with Excel macros • Created assembly quality training package videos documenting foreign and domestic object debris in aircraft engines, as well as defects in high-pressure compressor rotor blades