Space Tug Delta-v Budget Calculator
Assess propellant needs for orbital transfer and servicing missions by combining delta-v segments and applying contingency.
Preliminary mission estimator. Validate with detailed astrodynamics simulations and propellant management budgets before committing to flight plans.
Examples
- Final mass 4,200 kg, transfer 1,800 m/s, rendezvous 450 m/s, Isp 320 s, contingency 10% ⇒ Total delta-v 2,475.00 m/s, propellant 5,044.20 kg, launch mass 9,244.20 kg.
- Final mass 3,500 kg, transfer 1,500 m/s, rendezvous 300 m/s, Isp 340 s, contingency blank ⇒ Total delta-v 1,800.00 m/s, propellant 2,506.15 kg, launch mass 6,006.15 kg.
FAQ
Can I include multiple transfer legs?
Yes. Sum their delta-v contributions before entering the total transfer value, or rerun the calculator for alternative sequencing scenarios.
How does payload release affect the result?
The final mass should represent the tug after payload deployment. If payload drop-off is mid-mission, adjust the final mass or run separate stages to reflect staging effects.
What if the tug uses electric propulsion?
Electric tugs often have much higher specific impulse but lower thrust, which introduces gravity losses. Use mission analysis tools to translate low-thrust trajectories into an effective delta-v before applying this calculator.
Additional Information
- Result unit: metres per second for delta-v and kilograms for mass outputs.
- Assumes constant specific impulse and impulsive burns; incorporate finite-burn losses separately for low-thrust systems.
- Contingency margin scales all delta-v segments equally; adjust if certain phases carry different reserves.