Kostenloser Tsiolkovsky Equation Rechner
Finden Sie den required mass ratio for a given delta-v unter Verwendung von the Tsiolkovsky rocket equation. kostenloser Rechner.
Required Mass Ratio (m0/mf)
22.9504
Required Mass Ratio (m0/mf) vs Required Delta-V
Formel
## Tsiolkovsky Equation: Mass Ratio Form Given a target delta-v and an engine's exhaust velocity, this tells you how massive the rocket must be at launch relative to its dry mass. ### Formula **m0/mf = exp(dv / ve)** The fuel fraction is 1 - 1/(m0/mf). For orbital velocity (9.4 km/s) with a 3 km/s exhaust, over 95% of the rocket must be propellant.
Lösungsbeispiel
Reach LEO (dv = 9400 m/s) with ve = 3000 m/s.
- 01m0/mf = exp(dv / ve)
- 02m0/mf = exp(9400 / 3000)
- 03m0/mf = exp(3.133) = 22.94
- 04Fuel fraction = 1 - 1/22.94 = 0.9564 = 95.64%
Häufig Gestellte Fragen
What limits the mass ratio in practice?
Structural mass. Tanks, engines, and the payload set a floor for the dry mass. Typical first stages achieve mass ratios of about 8 to 12.
How does exhaust velocity affect the mass ratio?
Higher exhaust velocity dramatically reduces the required mass ratio. Doubling ve halves the exponent, which can reduce the mass ratio by orders of magnitude.
What is a typical exhaust velocity?
Chemical rockets: 2500 to 4500 m/s. Ion engines: 30 000 to 70 000 m/s, but with very low thrust.