Estimate propellant reserved for repeated station-keeping maneuvers over a mission and relate burn spacing to orbital period. The rocket equation captures mass depletion instead of multiplying fuel linearly.
Total Δv is annual station-keeping delta-v multiplied by mission years; g₀ = 9.80665 m/s².
The propellant result is the ideal rocket-equation allocation for the entered cumulative maneuver budget. Burn interval provides an operations cadence check based on orbital period.
Add reserves for disposal, collision avoidance, attitude control, and propulsion performance uncertainty separately.
A 500 kg spacecraft with 220 s specific impulse and 60 m/s total station-keeping delta-v needs about 13.71 kg of propellant. A burn every 500 orbits in a 95-minute orbit is about every 32.99 days.
Enter distance from the body's center. Add the body's mean radius to altitude before using the calculator.
Yes. It uses a two-body circular-orbit approximation unless the page explicitly asks for a mission allowance.
Yes. Replace the gravitational parameter and radius inputs with values for the selected body.
High-fidelity tools may include oblateness, atmospheric drag, third-body gravity, eccentricity, and numerical propagation.
No. They are preliminary engineering estimates and should be checked with validated mission-analysis software.
| Symbol | Meaning |
|---|---|
| m₀ | Initial wet mass |
| Isp | Thruster specific impulse |
| Δv | Cumulative station-keeping demand |
| g₀ | 9.80665 m/s² |