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sci.delta-v-Tsiolkovsky Calculator
Calculates rocket delta-v from the Tsiolkovsky rocket equation Δv = Isp × g₀ × ln(m₀/m_f) and required propellant mass for a given manoeuvre. To reach LEO (~9.4 km/s delta-v), a rocket needs m_prop/m_total ≈ 90% if Isp = 300 s (solids) or 60% if Isp = 450 s (cryogenic LOX/LH₂).
Inputs
M Wet Kg
Total mass (kg). Distinct from weight — weight = mass × gravity. Mass is constant; weight varies with location.
M Dry Kg
Total mass (kg). Distinct from weight — weight = mass × gravity. Mass is constant; weight varies with location.
Isp S
Reference formula or conversion factor shown for context.
Results
delta-v Δv (m/s)
The change in velocity a spacecraft can achieve using its propellant. The fundamental budget for orbital manoeuvres.
delta-v (km/s)
The change in velocity a spacecraft can achieve using its propellant. The fundamental budget for orbital manoeuvres.
mass ratio m₀/mf
The proportional relationship between two quantities.
propellant mass burned (kg)
The computed mass of the object or substance.
Δv = Isp·g₀·ln(m₀/mf)
ISP (specific impulse) — rocket engine efficiency in seconds. Higher ISP means more thrust per kilogram of propellant consumed.