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The rocket equation (Tsiolkovsky) relates rocket velocity change to exhaust velocity and mass ratio. It's fundamental to space mission planning and launch vehicle design.
Wzór
The calculator applies ΔV = v_e × ln(m_initial / m_final)
Przewodnik krok po kroku
- 1Enter initial mass, final mass, and exhaust velocity
- 2The calculator applies ΔV = v_e × ln(m_initial / m_final)
- 3Results show achievable velocity change
Rozwiązane przykłady
Wejście
v_e = 4000 m/s, m_initial = 100 tonnes, m_final = 10 tonnes
Wynik
ΔV ≈ 9,210 m/s
Sufficient for Earth orbit
Częste błędy do unikania
- ✕Using natural logarithm (ln) instead of log₁₀
- ✕Confusing initial mass with fuel mass
Często zadawane pytania
Why does mass ratio matter so much?
The logarithmic relationship means doubling the mass ratio roughly doubles the velocity change, making efficiency critical.
What determines exhaust velocity?
Exhaust velocity depends on propellant energy density and engine efficiency; chemical rockets are typically 3000-4500 m/s.
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