Calculate orbital transfers, delta-v requirements, and mission parameters for space travel.
Plan space missions by calculating Hohmann transfer orbits, delta-v requirements, travel time, and fuel consumption for orbital maneuvers.
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Transfer from Low Earth Orbit to Geostationary Earth Orbit, a common satellite mission.
Initial Orbit: 7000 km
Target Orbit: 42164 km
Spacecraft Mass: 1500 kg
Fuel Mass: 800 kg
Specific Impulse: 320 s
Central Body Mass: 5.97e24 kg
Hohmann transfer from Earth orbit to lunar orbit for lunar missions.
Initial Orbit: 6371 km
Target Orbit: 384400 km
Spacecraft Mass: 3000 kg
Fuel Mass: 1500 kg
Specific Impulse: 350 s
Central Body Mass: 5.97e24 kg
Interplanetary transfer from Earth to Mars orbit around the Sun.
Initial Orbit: 149600000 km
Target Orbit: 227900000 km
Spacecraft Mass: 5000 kg
Fuel Mass: 2500 kg
Specific Impulse: 400 s
Central Body Mass: 1.99e30 kg
Small satellite mission from ISS orbit to higher operational orbit.
Initial Orbit: 6771 km
Target Orbit: 8000 km
Spacecraft Mass: 100 kg
Fuel Mass: 50 kg
Specific Impulse: 280 s
Central Body Mass: 5.97e24 kg