Burnout Mass In The Context of Rocket Equation Calculator

The burnout mass of a rocket refers to the mass of the rocket at the moment when its propellant is completely consumed, and it marks the end of the powered phase of the rocket’s flight. The calculation involves considering the initial mass of the rocket (including the mass of the propellant) and subtracting the mass of the propellant burned during the flight.

This formula provides an estimate of the burnout mass, assuming a simplified model without considering factors such as air resistance, gravity losses, or structural mass changes. For more accurate results, these factors may need to be taken into account in a more detailed analysis.

Here’s the formula for calculating the burnout mass of a rocket in the context of the rocket equation, expressed in SI units:

Where:

• m_f is the burnout mass of the rocket (kg),
• m₀​ is the initial mass of the rocket, including propellant (kg),
• $\Delta V$ is the change in velocity required for the mission (m/s),
• I_sp​ is the specific impulse of the rocket engine (s),
• g₀​ is the acceleration due to gravity at the Earth’s surface (approximately 9.81 m/s^2)
• $e$ is the mathematical constant approximately equal to 2.71828.