Delta-V Calculator (Tsiolkovsky)
Rocket-equation solver for orbital maneuvers. Δv = Isp · g₀ · ln(m_wet / m_dry). Forward mode (given masses → Δv) and reverse mode (given Δv → propellant needed).
Inputs
Propulsion
Typical: 220-300s (monoprop), 300-340s (biprop), 1500-4500s (electric), 430s (LH2/LOX).
Masses
Result
Want to stage this, add finite-burn gravity losses, or schedule maneuvers against real ephemerides?
Sign up →Frequently asked questions
What is Tsiolkovsky's rocket equation?
Δv = v_e · ln(m_wet / m_dry), where v_e = Isp · g₀ is the exhaust velocity. It tells you how much velocity change a vehicle can produce given its initial and final mass, assuming a constant exhaust velocity (impulsive approximation).
Why does high Isp matter?
Propellant is exponential in Δv. Doubling Isp halves the mass ratio needed for a given Δv. That's why electric propulsion (Isp 1,500-4,500s) is transformative for deep-space and GEO missions despite low thrust.
What does this tool NOT account for?
Finite-burn gravity losses, atmospheric drag, steering losses, multi-stage vehicles, or variable thrust profiles. For real maneuver planning use the Finite Burn and Porkchop tools in the Aerospace Pack.
Upgrade for real maneuver planning
- Finite-burn gravity loss modeling
- Multi-burn maneuver sequencing with launch windows
- Hohmann, bi-elliptic, Lambert, and low-thrust solvers
- Porkchop plots for interplanetary transfers
- Export maneuver schedule to ops timeline