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Calculate delta-v, orbital periods, escape velocities, and satellite lifetimes with physically accurate formulas
Calculate the delta-v required for a Hohmann transfer orbit between two circular orbits around Earth. This is the most fuel-efficient two-impulse transfer between coplanar circular orbits.
Altitude above Earth surface (LEO: ~400 km, MEO: ~20,000 km)
Altitude above Earth surface (GEO: 35,786 km)
A Hohmann transfer uses two engine burns to move between circular orbits. The first burn at perigee raises the apogee to the target orbit altitude. The spacecraft coasts along the transfer ellipse for half an orbital period, then a second burn at apogee circularizes the orbit. This is the minimum-energy transfer between two coplanar circular orbits, requiring the least total delta-v. For the formulas: ΔV₁ = √(μ/r₁) * (√(2r₂/(r₁+r₂)) - 1) and ΔV₂ = √(μ/r₂) * (1 - √(2r₁/(r₁+r₂))), where μ = 398,600.4418 km³/s² and r = R_E + altitude.