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eng.rocket-delta-v-budget Calculator
Calculates the rocket delta-V budget for a multi-stage mission from launch, orbital insertion, and attitude control requirements. Total delta-V budget for a lunar mission is approximately 9.3 km/s — each mission phase contributes to the budget, which then drives the propellant fraction.
Inputs
Exhaust Velocity Ms
Speed in a specified direction (m/s). Required for momentum, kinetic energy, and wave calculations.
Mass Ratio
Total mass (kg). Distinct from weight — weight = mass × gravity. Mass is constant; weight varies with location.
Gravity Loss Ms
Reference formula or conversion factor shown for context.
Drag Loss Ms
Reference formula or conversion factor shown for context.
Results
ideal delta-v (m/s)
The change in velocity a spacecraft can achieve using its propellant. The fundamental budget for orbital manoeuvres.
actual delta-v (m/s)
The change in velocity a spacecraft can achieve using its propellant. The fundamental budget for orbital manoeuvres.
losses (m/s)
The decrease or degradation from the baseline.
Tsiolkovsky: Δv = Ve·ln(m₀/mf)
Sample size or count used in the calculation.
LEO delta-v requirement
The change in velocity a spacecraft can achieve using its propellant. The fundamental budget for orbital manoeuvres.
Isp = Ve/g₀
ISP (specific impulse) — rocket engine efficiency in seconds. Higher ISP means more thrust per kilogram of propellant consumed.