Tool Center

Ideal Rocket Equation

Inputs

Specific Impulse (ISP)

sec

Isp is how efficiently an engine/propulsion system can generate thrust.

Mass Initial

Mass of spacecraft before the burn or maneuver.

Mass Final

Mass of spacecraft after the burn or maneuver.

Outputs

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

Calculation Log


                satcatalog: python ideal_rocket_equation.py
                
                    
                    
                    exhaust_velocity = 180.00 s * 9.80665 m/s^2
                    
                    exhaust_velocity = 1765.20 m/s
                    
                    delta_v = 1765.20 m/s * log(105.0 kg / 75.0 kg)
                    
                    delta_v = 593.9 m/s
                    
                    mass_propellant = 105.0 kg - 75.0 kg
                    
                    mass_propellant = 30.00 kg