Tool Center

Ideal Rocket Equation

Inputs

sec

ISP = How efficiently an engine/propulsion system can generate thrust.

kg

Mass Initial = Mass of the spacecraft before the burn/maneuver.

kg

Mass Final = Mass of spacecraft after the burn/maneuver.

Outputs

Exhaust Velocity
1765.20 m/s
Delta V
593.94 m/s
Propellant
30.00 kg