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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.

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.

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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.
Transcribed Image Text: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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