Rocket Equation Calculator

The rocket equation is a fundamental equation in astronautics that describes the relationship between the mass of a rocket, the speed of its exhaust, and the resulting velocity change (delta-v) it can achieve. It is expressed as follows:

Parameters:

1. $\Delta V$ (Change in Velocity):
   • Definition: The change in velocity the rocket experiences during its powered phase.
   • Unit: meters per second (m/s).
2. I_sp​ (Specific Impulse):
   • Definition: A measure of the efficiency of a rocket engine. It is the thrust produced per unit mass of propellant consumed.
   • Unit: seconds (s).
3. g₀ (Acceleration Due to Gravity at Earth’s Surface):
   • Definition: The standard acceleration due to gravity on the Earth’s surface.
   • Value: Approximately 9.81 m/S².
4. m₀​ (Initial Mass of the Rocket):
   • Definition: The total mass of the rocket at the beginning of the powered phase, including the mass of the propellant.
   • Unit: kilograms (kg).
5. m_f (Final Mass of the Rocket or Burnout Mass):
   • Definition: The mass of the rocket at the moment when the propellant is completely consumed (burnout).
   • Unit: kilograms (kg).