The burnout mass of a solid propellant rocket engine is the mass of the rocket motor casing and any remaining structural components after the propellant has been completely consumed or burned during a rocket launch. This parameter is crucial in rocket design and performance analysis.
The formula to calculate the burnout mass Mburnout can be expressed as:
Where:
- is the burnout mass of the rocket motor (in kilograms, SI unit).
- is the initial mass of the rocket motor, including both the propellant mass and the casing mass (in kilograms, SI unit).
- is the mass of the propellant consumed during the rocket burn (in kilograms, SI unit).