Satellite Collision Avoidance Delta-v Calculator

Translate expected collision-avoidance manoeuvres into monthly delta-v demand and propellant draw using the rocket equation.

Mass at the start of the month including usable propellant.
Planned manoeuvre magnitude for a single dodge.
Expected executed collision-avoidance burns in the month.
Isp for the propulsion system; defaults to 220 s for monoprop thrusters.
Contingency added to total delta-v; defaults to 10%.

Mission-planning aid. Validate manoeuvre and propellant budgets with flight dynamics and operations engineering teams before committing to launch windows or service life claims.

Examples

  • Mass 320 kg, 0.35 m/s per burn, 8 burns/month, Isp 220 s, 10% margin ⇒ Total 3.08 m/s, propellant 0.45 kg (0.14% mass fraction).
  • Mass 250 kg, 0.8 m/s per burn, 4 burns, margin 15%, Isp left blank defaults 220 s ⇒ Total 3.68 m/s, propellant 0.95 kg (0.38% mass fraction).

FAQ

Should I include station-keeping burns?

This tool isolates collision-avoidance activity. Add your routine station-keeping budget separately to size total propellant reserves.

What if the spacecraft mass changes?

For small delta-v manoeuvres the mass change is tiny. If you expect major propellant drawdown, rerun the calculation with an updated mass mid-campaign.

How do I set the event count?

Use historical conjunction statistics per satellite, then add mission-specific modifiers such as solar-cycle drag or new debris fields that could raise avoidance frequency.

Additional Information

  • Result unit: total delta-v in metres per second plus propellant mass in kilograms.
  • Rocket-equation calculation assumes constant mass and Isp over the month; short burns make this approximation reasonable.
  • Delta-v margin defaults to 10% to cover dispersions or additional screening-driven manoeuvres.

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