Cold Gas Propulsion (CGP) systems use pressurized gas, often stored at cryogenic temperatures, to provide thrust. These systems are simpler than liquid or solid rocket engines but are often used for specific applications, such as attitude control systems or small-scale propulsion.
The burnout mass in the context of a Cold Gas Propulsion system would be the mass of the system after all the gas has been expelled. The formula to calculate the burnout mass Mburnout for a Cold Gas Propulsion system 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).
- is the mass of the propellant (which is in gaseous form) consumed during the rocket burn (in kilograms, SI unit).