Estimate propellant allocated to satellite-link mission support maneuvers such as antenna-geometry maintenance, station keeping, or disposal. Using spacecraft dry mass, cumulative maneuver delta-v, thruster specific impulse, and reserve, the calculator applies the ideal rocket equation to report loaded propellant, beginning mass, and mass fraction.
The main result is the loaded maneuver propellant attributed to the entered link-support delta-v. Beginning mass and propellant fraction help expose the mass impact on the spacecraft.
This allocation model does not establish that a maneuver is needed for a given link. Avoid double-counting delta-v already held in another station-keeping or disposal budget.
For a 500 kg dry spacecraft, 120 m/s cumulative delta-v, 220 s Isp, and 10% reserve, ideal propellant is about 28.60 kg and loaded propellant is about 31.46 kg.
It is a mission-defined allocation for maneuvers that preserve communications geometry or operations, such as station keeping or selected attitude-orbit actions.
Only if it is a separate requirement. Do not count the same maneuver delta-v in two allocations.
Include all mass remaining after usable maneuver propellant, following the project's mass-accounting convention.
Yes, if the entered delta-v and dry mass correspond to that propulsion case and operational effects are assessed separately.
It exposes the selected operational or uncertainty allowance separately from the ideal physics requirement.
| Input | Unit | Role |
|---|---|---|
| Spacecraft dry mass | kg | Mass remaining after usable maneuver propellant. |
| Cumulative support delta-v | m/s | Total allocated velocity change. |
| Thruster specific impulse | s | Effective Isp for the maneuver system. |
| Propellant reserve | % | Extra propellant above the ideal requirement. |