The rocket equation
Δv = Isp·g₀·ln(m_wet/m_dry) ⇒ m_p = m_dry·(e^(Δv/Isp·g₀) − 1)
g₀ = 9.80665 m/s². The exponential means propellant fraction explodes with Δv/(Isp·g₀): chemical propulsion is fine for hundreds of m/s, while km/s-class missions on small sats push you to electric propulsion — at the price of power (see the EP tool) and thrusting time.
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