rocket-propulsion

Solid, hybrid and detonation rocket propulsion models: Cantera thermochemistry, arbitrary grain burn-back, O/F control, printable nozzle CAD

Predicting and mitigating N2O flashing in hybrid rocket feed systems.

Conceptual design and analysis of a liquid-propellant rocket engine for orbital launch vehicles. Presents key specs (chamber pressure, nozzle expansion, thrust-to-weight), propellant/material selection (LOX/RP-1 & LOX/LH₂), cycle considerations, and computational workflows for engine sizing, sweeps and trade-off studies.

Open-source Python toolkit for thermodynamic modelling and performance analysis of Rotating Detonation Rocket Engines (RDREs)

A 100 kN solid rocket motor: ballistic design, thermal protections and a reusable water cooling jacket.

Native desktop workstation for compressible-flow analysis and liquid rocket engine preliminary design — PySide6/QML UI over a verified NASA CEA/Cantera thermochemistry, fluids, and propulsion performance stack.

Authority-controlled liquid rocket preliminary propulsion analytical toolkit with primary literature provenance (NASA SP-125, Bartz 1957, NASA SP-194).

Small validation slice of the SGK pre-design: PicoGK voxel geometry, feature extraction, analytical flow benchmarks with OpenFOAM cross-check.

A generative space propulsion design tool: 0D/1D physics to voxel geometry (PicoGK), neural surrogates, generative optimization. Open-source experiment, engine-family-agnostic.

Interactive aerospace mechanics simulation for the Tsiolkovsky rocket equation, variable mass dynamics, multi-stage optimization, and thrust vectoring.

SymPy-based lab for quasi-1D nozzle gasdynamics: symbolic isentropic relations, numerical profiles, and engineering plots.

3 DOF point-mass rocket flight simulator in MATLAB modeling atmospheric drag, inverse-square gravity, and propellant mass depletion.

Transient startup of a liquid-fueled rocket nozzle using a 2D axisymmetric compressible-flow. 1.1 MN of thrust

A CLI tool to calculate rocket propellant chemical energy, TNT equivalent mass, and blast yield using conversion efficiencies. Inspired by the New Glenn incident (May 2026).

Design and analysis of a throttleable spiral-vane pintle injector manifold for a LOX/LCH4 rocket engine — analytical feasibility, SolidWorks CAD, and a written technical report. 🚧 Ongoing.

Physics-informed propellant combustion and nozzle performance simulator with an optional TensorFlow surrogate for specific impulse. Computes exhaust velocity, thrust, Isp, temp/pressure profiles, wall heating, and stability spectrum for multiple propellants. CLI, plots, and cached models in models

Collection of my academic and technical projects in Aerospace Engineering, as well as Digital Twin modeling and other useful certificates.

Rocket propellant chemical equilibrium, thermodynamic and transport properties, and engine performance (NASA CEA's class of computation) for .NET, on CPU or CUDA in double precision. NuGet library and the apthermo command-line tool.

Minimal estimator of ideal (isentropic) rocket nozzle performance: exit state (Me, Pe, Te), CF, Isp, F/At, with Pc–area-ratio sweeps. Pure Python, small tests, CSV output for quick trade studies. Requires Python 3.10+.

CFD, thermal, and structural investigation of a high-enthalpy hydrogen propulsion system using ANSYS Fluent, ANSYS Mechanical, and MATLAB.