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🚀 Astronaut Rocket Equation & Delta-v Budget

🚀 Astronaut Rocket Equation & Delta-v Budget

Apply Tsiolkovsky’s rocket equation to wet mass, dry mass and specific impulse. Check ideal delta-v capability, propellant needed for a manoeuvre, reserve allowance and remaining mass.

Ideal capability
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Required incl. reserve
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Delta-v margin
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Propellant required
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Ideal single-stage vacuum equation Δv = Isp·g₀·ln(m₀/mf), with g₀ = 9.80665 m/s². It excludes gravity and drag losses, finite burns, boil-off, unusable propellant, staging, engine-out rules and trajectory constraints.

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