REMUS is a C++ simulation program designed to numerically model the motion of a rocket using the Rocket Equation. The program solves the system from time 0 until the rocket returns to h = 0. It incorporates environmental and rocket-specific parameters provided in a file called parameters.txt and integrates the system using the 4th-order Runge-Kutta scheme.

This project initially aimed to model a concept rocket for the Altitude Record Team's APEX I. APEX I successfully broke the UKRA I-Class record, achieving an altitude of 9333 ft (2845 m) and reaching Mach 1.55.

• Reads environmental and rocket-specific parameters from parameters.txt.
• Integrates the system using the 4th-order Runge-Kutta scheme.
• Writes time t and values of h, v, and m at each time step to the file output.txt.
• Includes user-defined classes for rocket and rocket stage representation.
• Extensible to model multi-stage rockets.

1. Ensure the parameters.txt file is in the current working directory with the specified format.
2. Run the REMUS program.
3. Check the output.txt file for the simulation results.

# Environmental parameters
1.22 9.81 0.2 0.0 0.0
# Rocket-specific parameters
2.0 0.0 0.001 0.005 100 0.01

If you are interested in contributing to REMUS, feel free to fork the repository and submit pull requests.

This project is licensed under the MIT License.

Special thanks to the Altitude Record Team for the real-world application of the Rocket Equation Model.