Solid Rocket Motor Simulator
Design and simulate solid rocket motors with BATES and Finocyl grain geometries. Analyze thrust curves, chamber pressure, and motor performance.
Grain Stack
No grain segments. Click "+ BATES" or "+ Finocyl" to add.
Motor Case
mm
Internal diameter of motor casing
cm³
Head-end free volume
Propellant
Density: 1625.09 kg/m³ | γ: 1.235 | Tc: 2616.5 K
High-performance APCP propellant
Nozzle Configuration
Automatically size throat for target pressure
psi
Leave blank for automatic optimization. Area ratio: exit area / throat area
Auto-sized dimensions:
Throat: 15.24 mm (0.600 in)
Exit: 76.20 mm (3.000 in)
Expansion: 25.0:1
Throat: 15.24 mm (0.600 in)
Exit: 76.20 mm (3.000 in)
Expansion: 25.0:1
Nozzle efficiency factor (typically 0.95-0.99)
psi
Add grain segments to enable simulation
Run simulation to see results
Sponsor
Cameron Rough
Cameron is a graduate student in Aerospace Engineering at Colorado State University.
Cameron was one of the principal authors of the Nexus Aurora report on a Martian City State presented at the 2020 Mars Convention.