PROJECTS

Overview: Pushing the boundaries of multi-material additive manufacturing by designing, optimizing, and digitally validating a micro-level linear solenoid actuator.

The Architecture: Engineered a highly condensed, circular-based coil embedded within a 0.01mm dielectric casing to eliminate structural current jumping while balancing strict thermal insulation constraints.

The Pipeline: Leveraged advanced SolidWorks CAD modelling alongside high-fidelity Ansys thermal-electric analysis and 2D Finite Element Method Magnetics (FEMM) simulations.

The Results: Successfully mapped critical performance parameters including current density thresholds, Joule heating profiles, and magnetic flux distributions proving our capability to solve complex, high-stakes micro-electronic design challenges.

Overview: Investigating the implementation of hidden “blind ports” within a solid fuel grain for hybrid rocket engines, specifically evaluating their structural and pneumatic effects on thrust, regression rates, and internal pressure throttling.

The Process: Modelled three distinct CAD iterations of the blind-port geometry alongside a baseline control fuel grain.

The Physics: Executed multi-variable burn simulations to map combustion chamber characteristics, internal operating pressures, and regression physics.

The Results: Validated the concept by demonstrating a measurable increase in both thrust and regression rates while safely stabilizing critical internal operating pressures.

Overview: Partnered with aerospace client KISPE to design, develop, and manufacture a compact satellite propulsion system for active collision avoidance onboard their OSSAT platform.

The System: Engineered a high efficiency resistojet system optimized to deliver the precise thrust vectors required for rapid collision avoidance manoeuvres and subsequent orbital restoration.

The Lifecycle: Successfully executed the entire engineering workflow spanning initial requirements writing and planning, to concept layout, detailed 3D CAD design, precision manufacture, and final hardware assembly.

The Results: Delivered a flight-ready propulsion subsystem that successfully meets all client orbital preservation constraints.

Overview: Conceptualizing and designing a high-integrity lunar lander mission engineered for the autonomous drilling, collection, and analysis of vital lunar ice.

The Integration: Tailored a custom structural lander layout specifically engineered to accommodate, protect, and deploy NASA’s VIPER rover as its primary payload.

The Validation: Conducted advanced environmental landing, structural integration, and deployment simulations to verify mechanical viability in extreme environments.

The Results: Produced a comprehensive digital data package confirming absolute structural integrity and mission feasibility.

Overview: Evaluating the physical plausibility of integrating an atmospheric air intake onto the Vega launcher’s first stage to replace or subsidize the heavy onboard oxidizer.

The Workflow: Modelled a complex intake manifold, including detailed system ducts and direct-feed lines to the main combustion chamber.

The Analysis: Subjected the entire assembly to rigorous verification using Computational Fluid Dynamics (CFD), supersonic shockwave analysis, and structural Finite Element Analysis (FEA) at both the component level and complete system level.

The Results: Proved the concept’s efficacy, demonstrating substantial launch mass reductions and increasing the available mass budget allocation for commercial payloads.

Overview: Developed a comprehensive, system-level computational architecture model to validate the feasibility of a 10-year Low Earth Orbit (LEO) Sun-Synchronous mission tracking global environmental metrics.

The Architecture: Synthesized multi-disciplinary spacecraft parameters including a 7-band VNIR optical payload, a green propulsion module, an on-board computer, and an S-band telecom link budget into an integrated mathematical trade-study matrix.

The Simulations: Leveraged Systems Tool Kit (STK) to model multi-variable orbital mechanics at a 500km altitude, proving that a ΔV profile of 97.48 m/s would effectively offset atmospheric drag and counter orbit decay.

The Optimization: Built dynamically linked mass and power budgets that optimized total platform layout down to 4.96kg (well under the strict 6kg launch limit) and mapped precise power loading profiles across varying orbital phases.

The Results: Delivered a rigorous, high-fidelity systems engineering framework that successfully verified full satellite lifecycle viability, baseline component margins, and eventual atmospheric re-entry requirements.