XCOMPUTE is a systems simulation and scientific computing platform that enables teams to resolve complex numerical problems with a modular approach to systems and algorithms. Unlike conventional computer-aided engineering (CAE) tools, XCOMPUTE is a complete, unified engineering environment, supporting mesh generation, fluid dynamics, stress mechanics, multiphysics and much more.XCOMPUTE's client-server model allows multiple users to view and collaborate on simulations using the graphical XC client, while the XC server solves simulations and can be deployed on local or cloud-based hosts.A spectrum of numerical methods are available for users to facilitate simulations, including:Galerkin Finite Element Method (FEM) for solid mechanicsFinite Volume Method (FVM) for Reynolds-Averaged Navier-Stokes (RANS) compressible gas dynamicsFinite Difference Method (FDM) for compressible Large Eddy Simulation (LES) and electromagnetism (E&M)Lattice-Boltzmann Method (LBM) for incompressible Large Eddy Simulation (LES)Level-Set Method (LSM) for implicit geometry representationDevice-agnostic SIMD Delaunay Triangulation for unstructured node colocationRegions can be linked to mediate data across physical domains, while CPU and GPU parallelism is exploited for computation and rendering. Patented heterogeneous data types and a polymorphic geometry kernel unify the XCOMPUTE platform.Recent engagements:-July 2022: International Conference for CFD (ICCFD11 Maui)-- published ICCFD11-2022-0802 "Algorithms and Instruction Sequences for CFD/FEA Multiphysics"-April 2019: Space Access exhibitor and presenter (Fremont)-July 2018: International Conference for CFD (ICCFD10 Barcelona)-- published ICCFD10-145 "Unified Geometries for Dynamic HPC Modeling"-April 2018: NASA Advanced Modeling & Simulation seminar (NASA Ames)-Feb 2018: Silicon Valley Space Center (Hacker Dojo)

Focus on delivering virtualized work technologies (integrated engineering environment) for massive space-based solar power constellations.

analytical, numerical, and experimental support for propulsion systems

Aerospace support contracts:-JPL / Caltech - custom optical amplifier instrumentation-Veritas - UAV flight computer systems-Odd Art Fabrications - OMAP3 embedded SPI hardware-software stack for arcade game-Virgin Galactic - Liquid rocket engine infrastructureCoauthored several unsuccessful proposals:-NASA SBIR 2011 on platelet injectors-NASA SBIR 2012 on isothermal propulsion (NTR, etc)-NASA SBIR 2012 on thermionic resonator (NEP, etc)-NASA BAA 2012 on advanced integrated nuclear-powered vehicle

System Engineer - 25,000 lbf “Necker-1” Liquid Rocket Engine Test FacilityEngineer/Analyst - Liquid Engine Subsystems & ComponentsExpedited facility and infrastructure design and build-out under VP Propulsion. Worked closely with managers for facility field fabrication in the Mojave Desert as cognizant engineer. Performed critical system-wide design/calcs/drawings for press & cryo systems up to 6000 psi. Worked closely with facility engineers to conceptualize, formalize, build, and field complex P&IDs. Responsible engineer on helium/ignition systems and general systems engineer for a dozen other major systems. Field labor (panels, orbital welding, cryo prep, etc) building facility from concrete slab to hotfire within 6 months. Established group standards in engineering component design and analysis. Provided ongoing general support across the Newton-1 engine system, calc checking, methodologies, etc. Most of this work became Virgin Orbit.

Structural Engineer - “GEEx” 165,000 lbf Rocket Engine Test FacilityGathered requirements and designed 165,000 lbf LOX/LH2 facility with 5x load margins. 60ft structure with 60 ft (300 kip) tanks on top. Performed critical operational and environmental load analyses with closed-form analysis, FEA, and AISC/ASCE references. Performed detailed design on columns, beams, joints, bolts, bracings, concrete. Produced drawings and bid packages for fabrication, selected vendors, cognizant field engineer on 1M lbm concrete work.Propulsion Engineer - “BE-3” LH2/LOX Rocket EnginePerformed internal hydrodynamic experiments to characterized large-scale turbulent behavior of engine cooling features. Planned, collected, and analyzed 200GB of data using high speed camera and autonomous processing in Matlab. Produced a 36-page report of results and recommendations to provide a jump-start on internal feature optimization in CFD.

Student Leader - Experimental Engineering DevelopmentTeam Leader - “Engineering Clinic” Applied ResearchABSTRACTHoneywell Aerospace produces induction motors for military aircraft. Conventional induction motor tests measure four discriminators on a fully assembled motor: current draw, power draw, torque and rotations per minute (RPM). Most motor failures are due to casting faults in the rotor. Thus, the Honeywell Clinic team seeks to research, design, build, and test an induction rotor quality control system. The system must test the rotor before full motor assembly and must distinguish between acceptable and unacceptable rotors as defined by the four parameters above. Final design utilizes a static coil-excited magnetic field to induce current in a single bar of the rotor and Hall-effect sensors to measure the resulting magnetic field strength. A fully functioning prototype has been completed along with experimental and theoretical justifications for the system. Design considerations and prototype construction are discussed along with preliminary results. Initial tests have revealed peak electromagnetic stability and bar width stability as two possible discriminators.Within a year, this technique saved Honeywell over a quarter million dollars.The year before, part of a clinic team with SwRI that developed an optical tracking system for planetary astronomy (using 2D lateral effect sensor and fast-steering mirror). Results were presented and published in Marseille with SPIE-7012 in 2008.

Instrumentation Technician - Mars Science Laboratory Descent Stage Test SystemsPrepared (wired, moved, installed) the electronic ground support equipment (command processor) for the MSL descent hydrazine propulsion system. Developed and installed various I&C systems. During qualification of Moog main valve in 2006, induction spikes damaged computer controllers. Quickly developed and delivered high-speed filter box to allow testing to continue, earning praise in JPL 353x management review. Instrumentation Engineer - Caltech's “Small Particle Hypervelocity Impact Range”Developed optical high speed switches and amplifiers to detect small (100um-500um) particles in the SPHIR flight tube at up to 10km/s. Developed novel differential filtering technique that eliminated 89% of electromagnetic noise during sensitive sampling, increasing the SNR (signal-to-noise ratio) by roughly 10 dB). The particles literally turn into plasma and create interesting E&M effects. I helped run the lab in basement of GALCIT or almost 2 years, making numerous contributions to the facility.Intern Technician - Dawn Spacecraft's Ion Engines GSEWorked alongside seasoned JPL spacecraft technicians through a variety of fluid systems prep and procedures in and around SAF and hazmat ops at 197. Soaked it all in without blowing anything up.