In a cold gas propulsion rocket engine, the propulsion is achieved by expelling a compressed gas, typically at ambient temperature, to generate thrust. These systems are often used in small-scale applications, such as attitude control for spacecraft. The mass flow rate for a cold gas rocket engine is determined by the rate at which the compressed gas is expelled.
The mass flow rate for a cold gas propulsion rocket engine is the rate at which the compressed gas is expelled from the rocket nozzle to generate thrust.
The mass flow rate for a solid rocket engine can be approximated as:
Where:
- ṁ is the mass flow rate (kg/s),
- is the density of the expelled gas (kg/m³),
- is the throat area of the nozzle (m²),
- is the effective exhaust velocity of the air through the nozzle (m/s).