rocket-propulsion

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

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.

Aerospike nozzle solver and geometry generator based on the 1963 C.C. Lee plug‑nozzle algorithm, with a modern Python implementation and a modular PySide6 GUI.

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

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

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

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

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

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.

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).

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.

Rocket staging optimizer CLI — find optimal engine configurations and propellant splits for multi-stage rockets using Tsiolkovsky's equation

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

Redline is a free, offline ground station for rocket static fires. It reads your stand live over USB, alarms when a channel crosses a limit you set, and works out burn time, total impulse, and motor class when the fire ends. Then it checks its own work and refuses to trust broken data. One HTML file, built by a 16-year-old.

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

Firehawk Aerospace — independent third-party profile of a public API surface, by API Evangelist. Firehawk Aerospace, Inc. is a Dallas, Texas defense-technology manufacturer founded in 2019 by Ronald Jones, Will Edwards and Steve Edwards that replaces conventional rocket-propulsion production with additive manufacturing.

🚀 Estimate ideal rocket nozzle performance with this minimal Python tool, calculating key metrics like thrust coefficient and specific impulse effortlessly.