Burnout Mass of a Solid Propellent Rocket In The Context of Rocket Equation Calculator

The burnout mass of a solid propellant rocket in the context of the rocket equation refers to the mass of the rocket after the solid propellant has been fully consumed. In the rocket equation, this parameter is crucial for understanding the performance characteristics of the rocket.

The rocket equation for a solid propellant rocket is:

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.