BE-7 Engine:•Ox turbopump assembly (OTPA) chill-in thermal-fluid model development and analysis for determining time to chill and total propellant consumption•Shutdown Valve steady state thermal analysis•Main Combustion Chamber (MCC) cooling thermal-fluid analysis for dual expander engine•Extensive anchoring of pressure drop, heat loads, and expected wall temperature to test data •developed improved methods and understanding for modeling additively manufactured cooling channels. Aspects of improved methodologies involve the development new Nusselt correlations for supercritical oxygen/hydrogen, roughness modeling for AM, and Nu augmentation from AM process

Project: Combustor Wall Cooling with Dirt Mitigation• Utilized Star CCM+ to model flows and dirt deposition behavior in double-walled effusion cooling combustor liners• Performed experimental tests on rig and performed analysis to evaluate deposition, flow parameter, and pressure behavior• Developed LabView program to monitor various properties (temp., pressure, etc.) during experimental tests

• Used ANSYS to perform transient thermal analysis on rocket nozzle to evaluate how different nozzle materials would behave• Explored and compared anticipated flow (atomization, impingement velocity) for 3 separate injector designs using ANSYS Fluent• Designed, analyzed, fabricated, and tested a reloadable pyrotechnic ignition device using a small solid motor to ignite our atomized liquid propellant• Manufactured in-house ablative liner and performed burn testing to validate performance under engine-relevant conditions

• Used ProPep to analyze various propellant compositions required to produce a 3kN APCP motor with 700psi chamber pressure• Use of Burnsim and in-house propulsion code to design and evaluate propellants thermodynamic properties and performance• Developed extensive solid propulsion development guidelines detailing all aspects of our project including chemical selection, casting procedures, safety considerations, analysis, etc.

Project: Low Creep/ Low Relaxation Polymer Composites for Deployable Structures•Studied viscoelastic properties of polymer composites to reduce the relaxation modulus for deployable booms on solar sails•Performed various carbon fiber layups to test how different matrices, ply orientations, and fortifiers affected relaxation•Use of DMA, SEM, and 3-point bend test to quantify relaxation results, visually inspect matrix-fiber adhesion, and test for interlaminar shear properties. •Investigated feasibility of composite support structures on lunar lander using SolidWorks and FEA simulations

•Designed a 38 mm minimum O.D. dual stage rocket to reach the highest altitude possible A.G.L. (est. 14,000 ft), limited by a total impulse of 640 N-s•Rocket parts and assemblies have been modeled using SolidWorks, flow and structural analysis done with CFD (SW Flow Sim) and FEA (SW), and dynamic flight analysis was performed using RockSim•Fabricated the nose cone, body tubes, and fins using fiberglass/carbon fiber lay-up methods and 3D print

• Using SolidWorks, I designed rocket airframe components and assembly for a rocket predicted to fly 10,000 ft, with trajectory and flight analysis being performed in RockSim software• I utilized FEA and CFD to study stresses present in critical areas of the rocket (fins, thrust plate, etc.) and optimized the fin design for better flow and structural rigidity • Fabricated custom composite carbon fiber fins by using a 3D printed mold layed-up in +45/-45 carbon fiber composite• Assisted in fabrication of general rocket assembly parts (propulsion section, thrust plate, boattail, etc.)

Tasked with developing a new method of thrust control for rockets, with specific applications being in solid and nuclear rockets. • Integrated a camera style iris mechanism into the throat of a rocket nozzle, shifting the flow area and varying the flow rate• Heavy utilization of CFD/FEA to analyze streamlines, Mach numbers, and deformation caused by large pressure gradients• Developed hybrid rocket propellant (acrylic/O_2) and a test stand to validate thrust variance induced by the device

Project: Utilize diffusion couples to identify the starting conditions on the final speciation of debris from a nuclear event.• Designed and machined a hot uniaxial press to eventually determine diffusion properties between nuclear fuel and cladding components for advanced fast neutron reactor fuels• Lab work involved experimentation and sample preparation through use of glovebox, furnace, and other preparation methods• Performed analytical scanning electron microscopy work to quantify diffusivity and diffusion coefficients within the uranium-based fuels and between fuel and cladding constituencies• Use of lathe and mills to fabricate steel enclosed chambers for samples

• Assisted groups of freshmen with hands-on activities such as arch bridge building, google app maker, smartphone programming, and drone programming• Facilitated conversations with freshmen, providing crucial advice regarding the challenges and benefits of pursuing a degree within the College of Engineering• Participated in the grading and judging of student's assignments, presentations, and projects

• Working in Enterprise Infrastructure Planning (EIP) which consist of project development, planning, and management• Innovated a streamline process for construction project lifecycles, enabling $100M in construction, and standardization across DOE• Tasked with scoping out entire projects, which includes determining the problem, solution, and identifying all constraints

• Formation of engineering standards for technical limitations and applications of materials, processes, methods, and designs• Creation of technical drawings via AutoCAD for engineering design standards and material data sheets• Active involvement with suppliers to locate items of need and verify design specifications

Mission: Design a payload to simulate a space probe entering atmosphere. It must: protect an egg during all portions of rocket flight, deploy and release a heat shield, and provide live telemetry feed.