Tool Center

Propellant Mass Calculator

Inputs

Sizing Method

Initial Spacecraft Mass Final Spacecraft Mass

Mass of spacecraft before the burn or maneuver.

Mass of spacecraft after the burn or maneuver.

Specific Impulse (ISP)

sec

How efficiently an engine/propulsion system can generate thrust.

Delta-V

m/s

Change in velocity for a specific burn.

Outputs

Exhaust Velocity: 1765.20 m/s
Propellant Mass: 11.55 kg
Spacecraft Final Mass: 188.45 kg

Calculation Log


                satcatalog: python propellant_mass_calculator.py
                
                    
                    
                    propellant_mass = 200.0 kg x (1-np.e^-(105.0 m/s / (180.0 s x 9.80665 m/s^2 )))
                    
                    propellant_mass = 11.55 kg
                    
                    final_mass_sc = 200.0 + 11.55
                    
                    final_mass_sc = 188.45