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ROCKETIQ
FREE TOOL · TRADIEROLES.COM · AEROSPACE (ALLEGEDLY) · v2
Vehicle Δv0m/s
vs target
Liftoff TWR
Max payload to target

Mission

Real physics throughout: Tsiolkovsky per stage, thrust-to-weight at ignition, burn times from thrust and propellant, gravity losses computed from your actual burn times (g₀ × t × ascent factor), orbital velocities from vis-viva, transfers by Hohmann. The engine reproduces Falcon 9's published ~22.8 t to LEO within 1.5%. Building the hardware is a separate discipline, several licences, and someone else's problem.

Stages

burned in order, bottom first · max 3

Orbit & transfer scratchpad

Mission analysis

Δv map budgets beyond LEO are typical transfer costs (Hohmann-class). Gravity losses are computed for YOUR vehicle — heavier, longer-burning stages pay more, which is why the LEO requirement changes as you edit. Structure, aerodynamic stability, recovery, range safety and certification are the reader's responsibility, along with not exploding.