Rocket Configuration
Presets
Number of Stages
Payload Mass5000 kg
Gravity Loss ΔVg300 m/s
Stage 1
Isp₁311 s
Propellant mass₁2141000 kg
Structural fraction ε₁0.060
Stage 2
Isp₂421 s
Propellant mass₂496000 kg
Structural fraction ε₂0.080
Stage 3
Isp₃421 s
Propellant mass₃107000 kg
Structural fraction ε₃0.100
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Total ΔV [m/s]
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Payload Fraction [%]
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Propellant Mass Ratio
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LEO Check
Equations
Tsiolkovsky equation (per stage): $\Delta V_i = I_{sp,i}\,g_0\,\ln\!\left(\dfrac{m_{0,i}}{m_{f,i}}\right)$
Structural mass: $m_{s,i} = \varepsilon_i \cdot m_{p,i}$
Effective ΔV = $\sum \Delta V_i$ − gravity loss − drag loss
Payload fraction = $m_{payload} / m_{total,0}$
Engineering Note: Propulsion mass budget verification for launch vehicle design. Use before STK, GMAT, or OpenRocket simulation to check staging strategy and ΔV allocation.