My doctoral research at Old Dominion University focuses on the characterization and optimization of a dual-cure epoxy system for rapid composite manufacturing. This material can be cured through conventional thermal processing or accelerated using a UV-activated catalyst, creating opportunities to reduce manufacturing time while maintaining control over material performance and part quality.

I use dielectric analysis (DEA) to monitor changes in ion viscosity, loss factor, permittivity, and in-situ temperature throughout thermal and UV-assisted cure cycles. These measurements are complemented by dynamic and isothermal differential scanning calorimetry (DSC), which provides information about reaction enthalpy, cure onset, peak reaction behavior, and residual cure. Together, these techniques help separate cure-driven material changes from temperature-dependent molecular mobility and provide the experimental foundation for cure-kinetics modeling.

The next stage of this work aims to examine how cure-cycle conditions influence chemical shrinkage, thermal expansion, and residual-stress development using bi-lamina testing and numerical modeling in Abaqus. The broader goal is to connect resin chemistry, processing conditions, and mechanical behavior to develop faster and more reliable manufacturing methods for high-performance composite structures.

For my senior mechanical engineering capstone project at Old Dominion University, my team investigated different manufacturing techniques for producing composite rocket airframes and structural components. The project focused on comparing the cost, repeatability, process complexity, and resulting component quality of several fabrication methods, with the goal of identifying practical approaches for manufacturing high-performance rocketry structures.

A major part of the project involved designing and building a low-cost filament-winding machine. After completing the initial system, we modified its mechanical and control systems to improve winding consistency, fiber placement, and overall operability. We used the machine to produce filament-wound airframes and compared the process with crank-assisted wet layup methods using carbon-fiber twill fabric and biaxial braided sleeves. We also manufactured composite panels using vacuum bagging and hot-press consolidation, including experiments with discontinuous-fiber reinforcement patterns.

Alongside the manufacturing work, I developed ply-level Abaqus models to examine how reinforcement arrangement and pattern geometry affected laminate behavior. By combining hands-on fabrication, process evaluation, and structural analysis, the project gave me experience connecting manufacturing decisions with the quality, repeatability, and expected performance of composite rocketry components.

In this side project, I investigated whether nickel and copper coated carbon-fiber veils can improve the thermal protection of epoxy composite panels. Panels containing the metal-coated veils are compared with control specimens made using pristine resin and uncoated carbon-fiber veils, allowing the effects of the metallic coatings to be evaluated independently.

Each panel undergoes a controlled torch-exposure test to compare heat transfer, surface degradation, and charring behavior. The resulting temperature response and visible burn damage are analyzed to determine whether the coated veils reduce heat penetration or improve resistance to thermal damage. This project provides practical experience in comparative materials testing while exploring a potentially lightweight method of improving the thermal resistance of composite structures.

This project investigated whether increasing the bonding area and mechanical interlocking at a metal–composite interface could improve the torsional strength of a bonded shaft assembly. Two metal shafts were wrapped with prepreg carbon fiber: one with a smooth bonding surface and the other with a dimpled surface designed to increase effective bonding area and promote mechanical engagement with the cured composite.

The completed specimens were loaded to failure in torsion to compare strength, failure location, and damage mechanisms at the metal–composite interface. Manufacturing complexity and process requirements were also considered to determine whether the dimpled texture offered a practical advantage over conventional surface preparation. As a limited comparative study, the project provided preliminary insight into joint behavior and helped identify the additional testing needed to establish statistical performance and cost effectiveness.

As part of a Fatigue and Fracture Analysis course, I designed and conducted a Mode I double-cantilever beam experiment to evaluate delamination growth in a unidirectional carbon-fiber composite. I compared several data-reduction methods for calculating the Mode I strain-energy release rate and apparent fracture toughness, including Simple Beam Theory, Modified Beam Theory, Compliance Calibration, and a Berry-method derivative approach.

This project gave me the opportunity to work through the complete experimental process, from specimen manufacturing and test preparation to crack-growth measurement, data analysis, and comparison of analytical methods. It provided valuable introductory experience in composite fracture mechanics and highlighted how assumptions within each reduction method can influence the reported results experience that will support more advanced fracture and durability studies in my future research.