Ignition time | s | ||
---|---|---|---|

Liftoff time | s | ||

Rod time | s | ||

Rod velocity | m/s | ||

Burnout time | s | ||

Burnout altitude | m | ||

Burnout velocity | m/s | ||

Total impulse | N·s | ||

Specific impulse | s | ||

Exhaust velocity | m/s | ||

Maximum G-load | G | ||

Apogee^{1} time |
s | ||

Apogee altitude | m | ||

Deploy time | s | ||

Deploy altitude | m | ||

Deploy velocity | m/s | ||

Landing time | s | ||

Landing velocity | m/s | ||

^{1}Apogee = maximum altitude |

This is a very simple model rocket simulation program. It takes published thrust curve data and interpolates that using cubic splines.

Features:

- dt = 10 ms
- g = 9.8 m/s²
- Air density calculation is based on a temperature lapse rate of -0.0065 K/m, so only valid up until 11 km.
- C
_{d}= 0.65 (DARK legacy)

Future improvements I'm considering:

- Complete modeling of the International Standard Atmosphere
- More detailed gravity model: Decreasing gravitational acceleration with altitude
- More rocket engines :)
- Real time simulation (with JavaScript!)
- Two-dimensional simulation for wind, downrange distance and gravity turn
- Actually measuring the drag coefficient of a real rocket
- Variable timesteps (Runge-Kutta, anyone?)
- Support for multistage rockets

Let me know what you think!