Chief Engineer
Current- Utilized Siemens NX for the design and implementation of an electronic remote disconnect system that allowed for the internal nitrous oxide tank of the rocket to be removed during take-off using a linear actuator and leadscrew-carriage design.- Initialized hydrostatic pressure relief test at 1500 PSI for validation of the internal aluminum bulkhead as well as the remote disconnect system and plumbing line attached.- Led and managed the mathematical modeling, computation, and design of the solid fuel grain used in the combustion chamber. This contained Hydroxyl-Terminated Polybutadiene and an MDI isocyanate mixed at a ratio of 85% curative and 15% HTPB. I then 3D printed a mold casting lined with cork insulation and cured the mixture under a vacuum chamber created by the team.- Led a team in conducting CFD using Ansys Fluent to analyze and validate different nose cones designs. Those analyzed were Von Karman, Elipse, Half power series, and Haack. We looked at pressure differentials along the tip and at fluid release points to determine which nosecone provided the least drag and fluid separation. - Created initial CAD assembly of a brand new system MSU rocketry has never attempted: Air brakes. This system uses a stepper motor to drive custom made brackets and airfoils that deploy throughout flight to slow the rocket and bring it closer to the 10,000 ft goal set by our competition. Conducted FEA using Autodesk Inventor Professional to determine the drag force and Von Mises stress created upon different values of air brakes deployemnt. I have 3D printed the first iteration and plan to further develop this project during FY25.