Rocket Equation for Solid Propellent Rockets Calculator

The rocket equation is a fundamental equation in rocketry that describes the relationship between the velocity of a rocket ($\Delta v$), the effective exhaust velocity of the propellant (ve​), and the initial and final masses of the rocket. The rocket equation for solid propellant rockets is derived similarly to other types of rockets, but the specific characteristics of solid rocket propulsion need to be considered.

The rocket equation is given by:

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).