Optimized Mass Breakdown
m₀ = m_dry × exp(Δv / (I_sp × g₀))
m_prop = m₀ − m_dry
m_payload ≤ m₀ × (target % / 100) − m_dry × overhead
Total initial mass (m₀)
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Propellant mass
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Max payload capacity
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Buffer margin
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Grounded in the Tsiolkovsky rocket equation principle. Analog: Paul R. Tregurtha—12,000-tonne ore carrier—where every tonne of cargo is a tonne less ice armor.