CubeSat Orbit Planner

Quickly assess a proposed CubeSat orbit. Provide altitude, mass, and drag area to derive orbital period, expected ground passes per day, ballistic coefficient, and an approximate atmospheric lifetime.

Mean circular-orbit altitude above Earth's surface in kilometres.
Total mass of the CubeSat including deployables in kilograms.
Average projected drag area in square metres across attitudes.
Typical CubeSat drag coefficient ranges from 2.0 to 2.5; override if you have wind-tunnel data.
Average thermospheric density at altitude (kg/m³); defaults to 5×10⁻¹² kg/m³.

Examples

  • 3U CubeSat at 500 km with Cd 2.2 ⇒ Period 94.62 min, lifetime ≈ 1,356 days
  • Drag-augmented deployment at 400 km ⇒ Period 92.56 min, lifetime ≈ 230 days

FAQ

How accurate is the lifetime figure?

Treat it as a first-order estimate. Use a numerical propagator with up-to-date space weather forecasts for mission assurance.

Why include drag coefficient as an optional input?

Cd depends on materials, deployables, and attitude. Overriding the default makes the ballistic coefficient reflect your specific design.

Can I model eccentric orbits?

No. The calculator assumes circular or near-circular LEO. Use a higher-fidelity propagator for eccentric trajectories with varying perigee density.

Additional Information

  • Orbital period assumes a circular orbit referenced to Earth's mean equatorial radius (6,378.137 km).
  • Ballistic coefficient equals mass divided by Cd × area, expressed in kg/m² and used for drag modelling.
  • Lifetime scaling is coarse—geomagnetic storms, attitude changes, and solar cycle variability can shorten decay dramatically.
  • Update the density term using MSIS, JB2008, or other thermospheric climatology that matches your mission epoch.

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