Numerical Simulation of a Two-Stage Rocket
This project simulates the vertical flight of a two-stage rocket by solving a system of ordinary differential equations (ODEs) numerically using scipy.integrate.solve_ivp with the RK45 method. The simulation accounts for quadratic air drag and gravitational forces but does not include parachute deployment during descent.
Project Structure
Functions
| Function | Description |
|---|---|
Calculations.one_stage() | Estimates motor delay (coast time), max velocity, and peak altitude for a one-stage rocket. Uses equations from RocketMime. A more accurate analysis requires numerical methods to account for dynamic mass. |
Calculations.two_stage() | Similar to one_stage(), but for a two-stage rocket. Uses equations from RocketMime. |
Input Parameters in data_run.py
| Parameter | Description |
|---|---|
| Rocket Stage Data | |
| Stage Area: Cross-sectional area of each rocket stage. | |
| Empty Mass: Mass of each stage without fuel. | |
| Engine Data | |
| 1st Stage Motor: CESARONI P38-4G WHITE THUNDER (I470) | |
| 2nd Stage Motor: CESARONI P38-5G BLUE STREAK (J357) |
This project provides a simplified yet insightful look into two-stage rocket dynamics using numerical methods.
The link for project code in Python is found in my repository: Two-stage rocket simulation with ODEs.