The burnout mass of a liquid propellant rocket engine refers to the mass of the rocket stage or engine casing and any remaining components after the liquid propellants have been fully consumed. Similar to the solid propellant case, the burnout mass is an important parameter in rocket design and performance analysis for liquid-fueled rockets.
The formula to calculate the burnout mass Mburnout for a liquid propellant rocket engine can be expressed as:
Where:
- Â is the burnout mass of the rocket motor (in kilograms, SI unit).
- Â is the initial mass of the rocket motor, including both the propellant mass and the casing mass (in kilograms, SI unit).
- Â is the mass of the propellant consumed during the rocket burn (in kilograms, SI unit).