Orbital Decay Calculator
Orbital Decay
Calculate the rate of orbital decay for a satellite in low Earth orbit due to atmospheric drag, estimating the remaining orbital lifetime.
Formula
Ballistic Coefficient = m / (Cd x A); Atmospheric Density = rho0 x exp(-h / H); Drag Deceleration = 0.5 x rho x v^2 x Cd x A / m
Frequently Asked Questions
What causes orbital decay?
Low Earth orbit satellites experience drag from the thin upper atmosphere. This drag removes kinetic energy, causing the orbit to gradually lower until the satellite reenters the atmosphere.
How does altitude affect orbital lifetime?
Atmospheric density drops exponentially with altitude. A satellite at 200 km may last only days, while at 600 km it can last decades. Above about 1000 km, decay takes centuries.
What is the ballistic coefficient?
The ballistic coefficient is the ratio of satellite mass to the product of drag coefficient and cross-sectional area. Higher values mean the satellite is less affected by drag and decays more slowly.
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