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Simplified orbital demo. Fixed approximate coplanar elements and a Sun-only two-body solver. Endpoint v∞ values are model encounter speeds, not spacecraft burns or mission-ready ephemerides. Planet sizes are enlarged for visibility.
Mission Earth → Mars
depart from
arrive at
Change either body or the launch/flight sliders to reset the animated flight. Inputs are bounded to 2026–2036 launches and 30–3000 flight days.
drag orbit · scroll zoom · focus canvas for arrow keys and + / − · H resets
Transfer —
—km/s combined endpoint v∞
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model cost · launch →↑ flight days
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Dark colors indicate lower combined endpoint v∞; light colors indicate higher values. Gray cells mean the demo solver did not converge. Click the plot, use arrow keys, or select a sampled candidate below.
This single-revolution demo omits planetary gravity, launch/parking-orbit burns, insertion burns, perturbations, vehicle limits and navigation uncertainty. The circular Hohmann reference is a teaching comparison, not a feasibility test. NASA trajectory terminology ↗