I aimed to create a computational model to simulate the launch of the Saturn V rocket. The model was developed based on a system of three thrusters responsible for propelling the rocket into lunar orbit.

Key Objectives:
1. Determine the total force of propulsion for the rocket, incorporating factors such as exhaust force and thrust.
2. Define the rocket's acceleration, considering gravitational forces and thrust.
3. Model the time-dependent mass of the rocket as it jettisoned thrusters and burned fuel.
4. Calculate the rocket's velocity and position over time using Euler's formula.

Results:
Model was successfully developed in MATLAB to simulate the Saturn V rocket's mission to orbit the moon. The model incorporated NASA-provided parameters and accurately assessed the rocket's acceleration, velocity, altitude, and fuel consumption over time. The model was divided into three main phases each corresponding to the one of the rocket's three thrusters. It accurately represented the transition between thrusters, accounting for jettisoning and ignition periods.

Key Findings:
1. Maximum altitude reached: 5,468 kilometers.
2. Maximum velocity achieved: 4,732.7 meters per second.
3. Thrust acceleration profiles for each thruster phase.
4. Fuel mass depletion over time.

More Info: For more information please see the report below.