Rocket Equation for Cold Gas Propulsion Rockets Calculator

The rocket equation for Cold Gas Propulsion (CGP) systems is derived similarly to other rocket equations but takes into account the specific characteristics of cold gas thrusters, which use pressurized gas expelled through a rocket nozzle for propulsion. In these systems, there is no combustion involved.

The rocket equation for Cold Gas Propulsion can be expressed as:

Where:

• $\Delta v$ is the change in velocity of the rocket (in meters per second, m/s).
• I_sp​ is the specific impulse of the rocket engine (in seconds, s).
• g₀ ​ is the acceleration due to gravity at the Earth’s surface (approximately 9.81 m/s29.81m/s2).
• m₀​ is the initial mass of the rocket (including propellant and structure, in kilograms, kg).
• m_f ​ is the final mass of the rocket (after propellant burnout, in kilograms, kg).