Turn an escape-trajectory delta-v requirement into ideal propellant mass with the Tsiolkovsky rocket equation. A separate reserve percentage shows the loaded propellant target without hiding the nominal physics.
Delta-v is converted from km/s to m/s; g₀ = 9.80665 m/s². Reserve is added to nominal propellant.
Nominal propellant is the ideal mass consumed to deliver the entered delta-v at constant specific impulse. The reserve result is a planning load, not a new rocket-equation solution.
Dry-mass constraints, residuals, mixture ratio, tank sizing, staging, gravity loss, and finite burns are not modeled.
A 1,000 kg wet spacecraft, 320 s specific impulse, and 3.2 km/s delta-v require about 639.45 kg nominal propellant. A 10% reserve raises the planning amount to about 703.40 kg.
No. Escape velocity is an ideal local speed; launch losses, staging, rotation, and the spacecraft's current speed change required delta-v.
No. The core escape calculation is a vacuum, two-body estimate. Add a mission margin or a separate loss estimate.
Yes. Enter that body's gravitational parameter and the distance from its center.
Gravitational potential becomes less negative with distance, so less kinetic energy is needed to reach a zero-energy escape path.
No. Use it for early trade studies, then verify with trajectory, propulsion, thermal, and operations analyses.
| Result | Interpretation |
|---|---|
| Nominal propellant | Ideal rocket-equation consumption |
| Reserve mass | Additional planning allowance |
| Loaded target | Nominal plus reserve |
| Final mass | Ideal post-burn mass |