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Example 4. A satellite is orbiting a circular orbit at an altitude of 900 km, at which atmosphere density is
5.46 x 10-13kg/m³. The satellite has mass 150kg, cross sectional area 1.50m², and drag coefficient 2.
a) Calculate the rate of change of orbit radius da/dt in units of m/s.
b) Make an estimate of the time (in years) that will take the satellite to reach the Earth.

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