Solid Rocket Motor Burnback Simulator

MATLAB prototype for simulating solid rocket motor (SRM) chamber pressure and propellant burnback. The code models pressure evolution and thrust curve as a balance between propellant gas generation and choked nozzle outflow, with geometry-dependent burning area and combustion chamber volume.

The repository currently contains both simple analytical grain models and a generic numerical solver using computational geometry algorithms and an ODE solver to simulate the burnback of complex geometries.

Files

File	Purpose
main.m	Main experiment script. Defines propellant/motor parameters, builds an example finocyl geometry, calls the ODE solver, and plots pressure and grain-state histories.
RocketSystem_Annular.m	ODE setup for an annular grain whose inner port grows while grain length regresses.
RocketSystem_Cylinder.m	ODE setup for a cylindrical/end-burning phase with pressure and remaining length as states.
RocketSystem_Generic.m	ODE setup intended to use arbitrary grain geometry/distance-field data.
genDistanceField.m	Helper for generating a signed distance field from an outer casing radius and inner-port polygon.
finocyl_pointy.m	Generates a 2D finocyl-style inner-port polygon with pointed fins.
configure.m	Configuration stub for distance-field resolution settings.

Requirements

• MATLAB
• Aerospace Toolbox, if using atmosisa from main.m
• An inpoly2 implementation on the MATLAB path, if using genDistanceField.m

Running

From MATLAB, open the repository root and run:

main

The intended output is a set of figures showing:

• chamber pressure versus time
• inner grain radius versus time
• outer grain radius versus time
• grain length versus time
• taper angle versus time

Safety Note

This is an engineering simulation prototype, not a validated motor-design tool. Use independent analysis, conservative margins, and qualified review before applying results to any physical rocket motor.