The rocket equation is a fundamental principle in astronautics that describes the relationship between the mass of a rocket, the effective exhaust velocity of its propulsion system, and the resulting change in velocity (delta-v).
Where:
- is the change in velocity (delta-v) that the rocket can achieve.
- is the effective exhaust velocity of the rocket propulsion system.Â
- is the initial total mass of the rocket, including both the rocket structure and the propellant it carries.
- is the final mass of the rocket, which is the mass of the rocket structure after expelling all of its propellant.