Orbital Decay Drag Lifetime Calculator
Space debris & LEO satellite operations: Calculate aerodynamic drag deceleration, ballistic coefficient ($B$), altitude loss per revolution ($\Delta a_{\text{rev}}$), and orbital lifetime until re-entry.
Satellite Mass & Cross-Section
CubeSat ~4 kg, SmallSat ~150 kg
Average projected ram area
Standard free-molecular flow: 2.2
Current LEO Orbit Altitude
Altitude above Earth reference sphere
Decay Rate & Remaining Lifetime
Estimated Orbital Lifetime:
--
until atmospheric re-entry
Altitude Loss Rate:
--
meters / day
Ballistic Coefficient B:
--
kg / m² (m / (Cd · A))
Atmospheric Density ρ:
--
kg / m³ at altitude h
| Atmospheric Scale Height H_s: | -- |
| Orbital Decay per Revolution: | -- |
| Orbital Velocity v_orb: | -- |
| Space Debris Compliance (25-Yr Rule): | -- |
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