Body & Orbit Settings
Central Body
Orbit Presets
Initial Orbit Radius r₁6571 km
LEO: 6571 km (200 km alt) / ISS: 6778 km
Target Orbit Radius r₂42164 km
GEO: 42164 km / Moon: 384400 km
Specific Impulse Isp450 s
Bi-elliptic Intermediate r_int100000 km
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ΔV₁ [km/s]
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ΔV₂ [km/s]
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Total ΔV [km/s]
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Transfer Time [h]
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Final Orbit Period [h]
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Propellant Fraction [%]
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Bi-elliptic ΔV [km/s]
Hohmann Transfer Equations
$\Delta V_1 = \sqrt{\dfrac{\mu}{r_1}}\left(\sqrt{\dfrac{2r_2}{r_1+r_2}} - 1\right)$
$\Delta V_2 = \sqrt{\dfrac{\mu}{r_2}}\left(1 - \sqrt{\dfrac{2r_1}{r_1+r_2}}\right)$
Transfer time: $T_{transfer} = \pi\sqrt{\dfrac{(r_1+r_2)^3}{8\mu}}$
Rocket equation: $\Delta V = I_{sp}\, g_0 \ln\!\left(\dfrac{m_0}{m_f}\right)$
Engineering Note: Foundation for satellite orbit design and mission analysis. Use before STK/GMAT simulation to verify propulsion mass budget and maneuver sequence planning.