Interplanetary Logistics
Choose a departure and an arrival window. We solve the transfer orbits, find the cheapest trajectory to Mars and price your shipment from the fuel it takes.
- Earth to Mars
- Transfer windows
- Open source
Transfer windows
Dates are UTC, between 1800 and 2050.
Launch window
Solving transfer orbits…
Estimated price
--€ / kg
Total Δv × -- € per kg for each km/s
Cheapest transfer
Departure--
Arrival--
Time of flight--
Total Δv--
Launch energy C3--
Arrival v∞--
Earth departure burn --
Mars capture burn --
Porkchop plot
Total Δv for every departure and arrival date in your windows. Brighter is cheaper; the ring marks the optimum. Hover to explore.
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Method and assumptions
- Cheapest single-revolution, prograde transfer between the planets, found by solving Lambert’s problem for every date pair, with impulsive burns.
- Δv covers departure from a 300 km circular Earth orbit and propulsive capture into a 300 km circular Mars orbit. No aerobraking, which would make the arrival burn cheaper.
- Planet positions come from the JPL approximate ephemeris. For the 2026–2034 windows it gives the same optimum dates as JPL’s full ephemeris and a Δv within about 1 m/s.
- C3 is the launch energy, the square of the excess speed leaving Earth. v∞ is the excess speed arriving at Mars.
- The method, its accuracy and the source code are on GitHub.